thruster pointing assembly requirement...

BC.ASU.SP.00010

Issue 1 of 77

Document Autogenerated from DOORS Module : /BepiColombo Implementation Phase/Level 3 Equipment Specifications/MPB/TPA BC_ASU_SP_00010_TPA_Specification_Formal_issue1_nonames_09_08_07.doc

THRUSTER POINTING ASSEMBLY REQUIREMENT SPECIFICATION

CI CODE: B3134 DRL Refs : EN-U16

UK EXPORT CONTROL RATING : Not Listed

Rated By :

Prepared by: Date:

Checked by: Date:

Approved by: Date:

Authorised by: Date:

This document is produced under ESA contract, ESA export exemptions may therefore apply. These Technologies may require an export licence if exported from the EU

© Astrium Limited 2007

Astrium Ltd owns the copyright of this document which is supplied in confidence and which shall not be used for any purpose other than that for which it is supplied and shall not in whole or in part be reproduced, copied, or communicated

to any person without written permission from the owner.

Astrium Limited, Registered in England and Wales No. 2449259 Registered Office: Gunnels Wood Road, Stevenage, Hertfordshire, SG1 2AS, England

BC.ASU.SP.00010Issue 1

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Astrium Ltd owns the copyright of this document which is supplied in confidence and which shall not be used for any purpose other than that for which it is supplied and shall not in whole or in part be reproduced, copied, or communicated to any person without written permission from the owner.

BC_ASU_SP_00010_TPA_Specification_Formal_issue1_nonames_09_08_07.doc

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CONTENTS 1 INTRODUCTION AND SCOPE................................................................................................................. 6

1.1 INTRODUCTION................................................................................................................................ 6 1.2 SCOPE............................................................................................................................................... 6

2 DOCUMENTS ........................................................................................................................................... 7 2.1 Applicable documents ........................................................................................................................ 7 2.2 Reference document.......................................................................................................................... 7 2.3 Standards (Reference)....................................................................................................................... 8

2.3.1 Space Engineering...................................................................................................................... 8 2.4 Abbreviations (see also AD46) .......................................................................................................... 8

3 Subsystem and Unit Functional and Performance Requirements .......................................................... 10 3.1 Hardware Definition.......................................................................................................................... 10 3.2 Functional Requirements ................................................................................................................. 10

3.2.1 Representitive thruster mass and inertia dummy ..................................................................... 11 3.2.2 Fuel and Harness lines ............................................................................................................. 11 3.2.3 Power consumption .................................................................................................................. 12 3.2.4 Power Budget ........................................................................................................................... 12 3.2.5 Motor Windings ......................................................................................................................... 12 3.2.6 Thermostat controlled Heaters ................................................................................................. 12 3.2.7 Position Monitoring and Characterisation................................................................................. 12 3.2.8 Reference Position.................................................................................................................... 13 3.2.9 Mechanical end stops and limit switches.................................................................................. 14 3.2.10 Hold Down and Release System (HDRM)................................................................................ 14 3.2.11 Thruster axis ............................................................................................................................. 14 3.2.12 TPM launch position ................................................................................................................. 15 3.2.13 Pointing Requirements.............................................................................................................. 15 3.2.14 Unpowered Holding Torque...................................................................................................... 17

3.3 Physical Characteristics ................................................................................................................... 17 3.3.1 Mass Properties ........................................................................................................................ 17 3.3.2 Equipments supported by the TPM .......................................................................................... 17

3.4 Interface Requirements.................................................................................................................... 18 3.4.1 Electrical interface description .................................................................................................. 18 3.4.2 Mechanical Interface................................................................................................................. 20 3.4.3 MCS Physical Reference Frame .............................................................................................. 21 3.4.4 Interchangeability...................................................................................................................... 22

3.5 Performance Requirements ............................................................................................................. 22 3.5.1 TPM Pre-release Stiffness........................................................................................................ 22 3.5.2 TPM Post-Release fundamental frequency. ............................................................................. 22 3.5.3 TPE fundamental frequency ..................................................................................................... 23 3.5.4 Reliability................................................................................................................................... 23 3.5.5 Lubrication ................................................................................................................................ 23 3.5.6 Outgassing................................................................................................................................ 23 3.5.7 Fatigue ...................................................................................................................................... 23 3.5.8 Corrosion of Materials............................................................................................................... 24 3.5.9 Dissimilar Metals....................................................................................................................... 24 3.5.10 Output Torque........................................................................................................................... 24 3.5.11 Testing in 1G Environment ....................................................................................................... 24 3.5.12 Structural Requirements ........................................................................................................... 24 3.5.13 Structural Analysis .................................................................................................................... 25 3.5.14 Isolation..................................................................................................................................... 25 3.5.15 Grounding and Bonding............................................................................................................ 25 3.5.16 EMC Environment..................................................................................................................... 25 3.5.17 EMC Performance Requirements............................................................................................. 25 3.5.18 Radiation Environment.............................................................................................................. 26 3.5.19 Margins of Safety ...................................................................................................................... 26 3.5.20 Resistive torque ........................................................................................................................ 26


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3.5.21 Factors of safety ....................................................................................................................... 26 3.5.22 Thermal Performance Requirements........................................................................................ 27 3.5.23 Life ............................................................................................................................................ 29 3.5.24 Protective Functions ................................................................................................................. 31 3.5.25 EEE Parts ................................................................................................................................. 31 3.5.26 Single Event Effects (SEE) ....................................................................................................... 31 3.5.27 Thermal Environments.............................................................................................................. 31 3.5.28 Actuator Backlash ..................................................................................................................... 31 3.5.29 Optical alignment cube. ............................................................................................................ 31 3.5.30 Failure Tolerance ...................................................................................................................... 31

3.6 Environmental Conditions ................................................................................................................ 32 3.6.1 Thermal environment (Extreme temperatures and maximal thermal gradients) ...................... 32 3.6.2 Vibration Environments............................................................................................................. 33

4 Product Assurance Requirements........................................................................................................... 37 4.1 Project Quality.................................................................................................................................. 37 4.2 Storage............................................................................................................................................. 37

5 GSE Requirements ................................................................................................................................. 38 5.1 Ground Handling .............................................................................................................................. 38 5.2 Transportability................................................................................................................................. 38

6 Verification Requirements ....................................................................................................................... 39 6.1 Surveillance, and Witness of Inspection and Test ........................................................................... 39 6.2 Cleanliness Requirements ............................................................................................................... 39 6.3 Verification Matrix............................................................................................................................. 39 6.4 Test Requirements........................................................................................................................... 39 6.5 Configuration and Data Management (CADM)................................................................................ 42

7 GDIR Applicability Matrix......................................................................................................................... 43 8 E&T Applicability Matrix........................................................................................................................... 59 9 EMC Applicability Matrix.......................................................................................................................... 66

TABLES Table 3.6-1: Random qualification test level and duration (Ref ECSS E 10 03A p.58) ................................. 34 Table 3.6-2: Sine ............................................................................................................................................ 35 Table 3.6-3: Random...................................................................................................................................... 35 Table 3.6-4: Shock.......................................................................................................................................... 36

FIGURES Figure 3.2-1: TPM / thruster in reference position......................................................................................... 13 Figure 3.2-2: TPM inclined mounting.............................................................................................................. 14 Figure 3.2-3: Thruster direction at Launch ..................................................................................................... 15 Figure 3.4-1: TPM to TPE(MCU) harness routing and length ........................................................................ 19 Figure 3.4-2: TPM deployed stay out volume 3D model DT0285635-01....................................................... 20 Figure 3.4-3: TPM/Thruster in its launch position prior to LVA release. 3D model DT0285634-01............... 21 Figure 3.4-4: MCS co-ordinate system........................................................................................................... 22 Figure 3.6-1: Shock environment ................................................................................................................... 35


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1 INTRODUCTION AND SCOPE

1.1 INTRODUCTION

This document defines the requirements applicable for the Thruster Pointing Assembly (TPA) to be used as part of the BepiColombo MTM Electric Propulsion System (MEPS).

BepiColombo is ESA’s cornerstone mission to Mercury to be launched in 2013.

1.2 SCOPE

This specification defines performance requirements, design and construction of the Thruster Pointing Assembly (TPA), which comprises Thruster Pointing Mechanisms (TPM) and the associated Thruster Pointing Electronics (TPE), along with all interconnecting harnesses and switches. The TPA is part of the MEPS for the BepiColombo Mercury mission. There are four Thrusters each with its own TPM.

The specification defines the performance and functional requirements, environmental requirements, interface requirements, ground support equipment requirements and performance verification.


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2 DOCUMENTS

2.1 Applicable documents

TPA-37//

The following documents form part of this specification. In the event of conflict between this specification and any applicable document, the discrepancy shall be notified to Astrium for resolution.

TPA-38//

List of applicable documents at current issue: within this specification applicable documents will be referred to as (ADn).

AD Title Doc-No

AD 01 General Design and Interface Requirements (GDIR)

BC-ASD-SP-00001

AD 02 Environment Requirements and Test Specification

BC-ASD-SP-00002

AD 03 EMC Requirements Specification

BC-ASD-SP-00033

AD 04

AD 05 Thermal Model Specification BC-ASD-SP-00030

AD 06

AD 09 SW PA Requirements for Subcontractors

BC-ASD-SP-00009

AD 11 NASTRAN Model ADS.E.0787

AD 12

AD13

AD 18 PA Requirements for Subcontractors

BC-ASD-SP-00018

AD 20

AD 21

AD 46

AD 49

2.2 Reference document

List of reference documents at current issue: within this specification, reference documents will be referred as RDn.

RD Title Doc-No

RD 01 BepiColombo project acronyms

BC-ASD-LI-00003

RD 10 ESA Pointing Error Handbook

ESA-CR(P)1364


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2.3 Standards (Reference)

2.3.1 Space Engineering

ECSS-E-30 Part 1A, Thermal Control, 25 April 2000

ECSS-E-30 Part 2A, Structural, 25 April 2000

ECSS-E-30 Part 3A, Mechanisms, 25 April 2000

ECSS-E-30 Part 5.1A, Propulsion - Liquid and electric propulsion for spacecraft, 2 April 2002

ECSS-E-30 Part 6A, Pyrotechnics, 25 April 2000

ECSS-E-30 Part 7A, Mechanical parts, 25 April 2000

ECSS-E-30 Part 8A, Materials, 25 April 2000

2.4 Abbreviations (see also AD46)

Abbreviation Description

AD Applicable Document/Drawing

AOCS Attitude Orbit and Control System

AIT Assemble Integration and Test

AOCS Attitude Orbit Control System

BB Breadboard

BOL Beginning Of Life

CI Configured Item

CoG Centre of gravity

EM Engineering Model

EMC Electro Magnetic Compatibility

EMI Electro Magnetic Interference

EOL End Of Life

ESD Electro Static Discharge

FM Flight Model

FMECA Failure Modes, Effects and Criticalities Analysis

GDIR General Design and Interface Requirements

GSE Ground Support Equipment

HDRM Hold down release mechanism

HW Hardware

I/F Interface

MCCS Mercury Cruise Composite S/C

MCS Mercury Composite Spacecraft

MCU MEPS control unit

MEPS MTM Electric Propulsion System

MOL Middle Of Life

N/A Not applicable

P Primary


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Abbreviation Description

Para Paragraph

PCDU Power Conditioning and Control Unit

PFM Proto-Flight Model

PPU Power Processing Unit

R Redundant

RD Reference Document/Drawing

S/C Spacecraft

SCU Spacecraft Computer Unit

SEP Solar Electric Propulsion

SEPT Solar Electric Propulsion Thruster

SPF Single Point Failure

TBC To Be Confirmed

TPA Thruster Pointing Assembly

TPE Thruster Pointing Electronics

TPM Thruster Pointing Mechanism

URD User Requirement Document


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3 SUBSYSTEM AND UNIT FUNCTIONAL AND PERFORMANCE REQUIREMENTS

TPA-219/CREATED/T,A,R

The TPA design and performance shall comply with the performance, functional, electrical and mechanical requirements detailed in the specification when subjected to the worst case environmental specifications contained in this document.

Four SEP thruster pointing mechanisms (TPM) are required, one for each of the four SEP thrusters. The preferred concept will incorporate a launch lock, and be capable of a pointing range shown in TPA-450.

3.1 Hardware Definition


The TPM shall provide independent two axis steering capability for each of the BepiColombo Solar Electric Propulsion Thrusters (SEPT). Each TPM shall provide pointing in two axes.

The Astrium MTM Electric Propulsion System (MEPS) control will be implemented by means of high-level commands from the spacecraft On-board Computer (OBC), with lower level control being performed by closed loop software control within the MEPS Control Unit (MCU).

TPA-223/CREATED/T,A,I,R

The TPA includes 4 TPMs, each of which shall include:

• Launch lock to protect the TPM and thrusters during the launch loads

• Two actuators with a drive mechanism. Stepper motors with redundant windings shall be.

• A two axis gimbal structure, allowing motion in two degrees of freedom.

• A position sensing device to provide position data on both axes.

• Structural support hardware internal to the TPM as required to meet the requirements within this specification

• Thermal control hardware internal to the TPM as required to meet the following requirements. All heaters used for thermal control shall be functionally redundant. Each independently controlled heater shall have a dedicated temperature sensor input to telemetry.

• Grounding and bonding hardware

• TPA Harness

• TPE boards which are commanded by, and housed in the MCU. See TPA-232

3.2 Functional Requirements

TPA-2601/CREATED/T,A

The TPA shall be designed to function within the constraints of the GDIR (AD1) supplied by the Customer and shall meet the following requirements:

TPA-232/CREATED/T,A

• Redundant thruster pointing electronics (TPE) are required

• The TPE shall ensure that both axes of any 2 out of the 4 TPMs can be actuated simultaneously, even in the event of any single failure.

• The Contractor shall investigate one to one connection and any other proposed connection methods between the TPE and the TPMs which meet the above functional requirements and which may reduce the overall system mass or cost. The Contractor shall provide a Trade Off with justification for the proposed interconnection scheme.

• The PCDU will command TPM HDRM release.


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• The TPE will include an interface to the 28V supply within the MCU and any necessary internal supplies.

• The TPAs shall include all cable harnesses, interface connectors and switches for connecting the TPE to the TPMs (this shall include all power and signal lines, i.e. actuators, position indicators, etc.).

TPA-243/CREATED/T,A

The Thruster Pointing Electronics (TPE) shall contain all the necessary electronics to drive the TPM stepper motor and will be commanded by the MCU via a Standard Balanced Digital link (TBC).

3.2.1 Representitive thruster mass and inertia dummy

TPA-388/CREATED/T,A

The TPM shall be analysed and tested with a representative thruster mass and inertia dummy attached to it. ICD to be provided for the thrusters. See TPA-2917

3.2.2 Fuel and Harness lines


The overall approach for the SEPS pipework and harness responsibilities is as shown in Appendix J of BC-ASU-SW-00001.

Space for the routing of the SEPS harness and fuel lines between the base of the TPM and the Thruster shall be provided to the side of each TPM within the allowable envelope of TPA 2818 .

The number of fuel pipes and harness lines is dependent on thruster selection.

The routing of the SEPS pipework and harness across the TPM shall be defined, designed (including mechanical analysis) by the TPA Contractor to comply with the allowable torque margins stated in TPA 429.

The following information shall be supplied to the TPA Contractor

• Mechanical characteristics

• Minimum bend radii

• Routing volume restriction

• Maximum unsupported lengths

• Definition of radiation protection needs/shielding

• SEPS pipework and harness thermal data

Supports which are to be mounted onto the TPM, these shall be considered to be part of the TPM.

Fatigue life testing of the SEPS pipework and harness is to be performed by the TPA Contractor, in conjunction with the TPM life test. The pipework and harness hardware for this test will be supplied by the Customer; the TPA Contractor is responsible for routing and supporting these items in accordance with the flight design. Functional tests of the pipework and harness required during this life test will be defined by the Customer; these will include visual inspection; flow and leakage (for the pipework), and electrical characteristics (for the harness).

The need for feed line shielding shall be defined in the form of an ICD and supplied by the Customer.

TPA-2685/CREATED/T,A

The TPA Contractor shall take into account the maximum allowable unsupported length (straight and helical) for any pipework and harness, which will be defined, in the pipework and harness routing, and identify any additional supports required.


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If the required supports as defined above are to be located on the mechanism, the contractor shall provide these items as part of the TPA

Any other additional supports (i.e. to the spacecraft structure) are provided by the Customer

3.2.3 Power consumption

TPA-253/CREATED/T,A

Power consumption shall be calculated with simultaneous actuation on both axes.

3.2.4 Power Budget

TPA-255/CREATED/T,A

• The TPA shall not consume more than 110W peak when operating up to 2 TPM simultaneously, each TPM being actuated on both if its 2 axes simultaneously

• The TPA shall not consume more than 21W average when operating up to 2 TPM simultaneously, each TPM being actuated on both if its 2 axes simultaneously, at a command rate of TBD

• The above power requirements shall include all elements of the TPA (including but not necessarily limited to TPM motors, position sensors, TPE losses and any internal thermal control heaters required, as discussed in section 3.5.22.7)

• Each TPM shall not consume and dissipate more than 50W peak, 8W average.

• The TPEs shall not dissipate more than 10% of the peak power figures identified above

• The following duty cycle at maximum speed should be used for initial assessments of peak/average power consumption and associated thermal impacts.

• Continuous operation of two TPMs for a duration of 1 hour; this includes the movement of the thrusters to their nominal position and a stabilization phase; this is followed by

• Small movements of plus or minus 0.1 deg every 5 minutes (300 sec) of two TPMs for a duration of 1 month.

• After this period a re-configuration (use of different thrusters) will become necessary, and the cycle is repeated.

3.2.5 Motor Windings

TPA-273/CREATED GDI-2240, Derived/T,A,R

Each of the TPM motors shall have a prime and redundant winding. These shall be wired as separate prime and redundant circuits and the failure of one circuit shall not be detrimental to the remaining winding. See GDI-2240 for Insulation requirements of motor windings

3.2.6 Thermostat controlled Heaters

TPA-275/CREATED/T,A

Thermostat monitored heaters shall be redundant and fail safe such that they cannot stay on following a failure. Power bus protection is required to prevent heater failures overloading the power bus.

3.2.7 Position Monitoring and Characterisation

TPA-3433//

Position monitoring shall be provided by absolute position sensing devices (Baseline) or by reference position sensors (Option) (See Cover letter Annex 2: Mandatory Options).


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TPA-794/CREATED GDI-3111 Derived/T,A,R

The TPM shall be equipped with absolute position sensing devices on both axes with an accuracy of ± 0.01° or better over complete range(GDI-3111). See Cover letter Annex 2: Mandatory Options

TPA-2959//

The output from the position sensing devices shall be recorded and provided by the contractor at the position defined in TPA-445, 2814

TPA-3432//

In the case of the reference position sensor Option (Cover letter Annex 2: Mandatory Options). A reference position sensor with bi level status shall be provided with an accuracy of 0.05 degrees, so that in the case of power shut down, the reference position sensor will indicate on which side of the reference position the TPM is pointing.

3.2.8 Reference Position


The Reference position corresponds to the centre of the required pointing range for each TPM.

If the TPMs can be accommodated within the allowed envelope with the axes of rotation parallel to the X and Y axes then the requirement is determined by the adjacent thruster firing angle requirements. This configuration will be beneficial in minimising the TPM pointing range to +/- 14.5 degrees on each axis independantly with a wedge of 6.6 degrees.

If the TPM cannot be accommodated within the allowed envelope with the axes of rotation parallel to the X and Y axes then the angular coverage to provide the pointing needs to be a worst case of +/-17.0 degrees conical shape in the Y and the X axis with a wedge of 9.14 degrees. This orientation is shown below.

THRUSTER FLOORTHRUSTER FLOOR

+/-17 Degree angle (TBC). Nominal position for thruster, Perpendicular to 9.14 degree (TBC) wedge





Figure 3.2-1: TPM / thruster in reference position


The Contractor shall supply as part of the TPM the inclination as described in TPA-445 and also shown below. The preferred method would be to include this as part of the TPM structure. An option would be to supply additional wedge/spacers as shown.


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9.14 degree wedge (TBC ), typical. 4 positions9.14 degree wedge (TBC ), typical. 4 positions Figure 3.2-2: TPM inclined mounting

3.2.9 Mechanical end stops and limit switches


End stops shall be required to avoid interference with SEPS parts and travel out of the specified envelop + limit bending of thruster feed lines + limit the angular range to the one specified.

Driving into mechanical end stops is acceptable provided it does not cause damage/degradation, or inhibit driving back from the stops. If damage will occur, then the TPM shall include redundant limit switches, installed instead of mechanical end stops.

The End stop position tolerance shall be + 0.0 to +0.3 degrees added to extremes of X and Y actuator axis. If limit switches are to be used they shall operate within the same tolerance stated above.

3.2.10 Hold Down and Release System (HDRM)


The HDRM shall secure the TPM in its stowed position (Launch position) during launch until commanded to release. The release devices shall be Non Explosive Actuators with an electrically redundant release design.

TPA-368/CREATED/T,A

The electrical firing current requirements shall be compatible with the standard pyrotechnic firing circuit defined in GDIR (AD1), and is sequential. The sequential release of each hold down shall not cause damage or risk of successful release.

TPA-369/CREATED/A

The movement of any structure during release must comply with the required allowable dynamic envelope described in TPA-2818

TPA-370/CREATED/A,I,R

Access must be ensured to allow easy removal and replacement of the release components.

3.2.11 Thruster axis

TPA-2816/CREATED/T,A,I

The two axes of TPM rotation shall intersect the thruster centreline. Tolerance zero to 0.3mm (TBC).


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3.2.12 TPM launch position


The locked position of the TPM for launch shall be with the thruster centre line parallel to the S/C Z axis.


9.14 Degree (TBC)wedge

Thru

ster

Lau

nch

Dire

ctio

n Perpendicular to thruster floor


9.14 Degree (TBC)wedge

Thru

ster

Lau

nch

Dire

ctio

n Perpendicular to thruster floor

Figure 3.2-3: Thruster direction at Launch

3.2.13 Pointing Requirements

TPA-450/MPB Derived CREATED/T,A,R

A summary of the key pointing requirements is given in the table below based on the combined performance of the TPM and TPE.

The ability to drive the TPM actuators singly or together is required.

Requirement Description

Accuracy (note 1) <=0.05°

Required resolution <= 0.01°


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Requirement Description

Angular range of motion required for 4 TPM's

+YSUN 362.75

#a

#c

362.75

26

26

513

CoG

+X

#d

#b zi u

4

° o

4 l

e i .

. E3

Azimuth -7.93° to 97.93°

°

Azimuth

-7.93° to 97.93° .

Azimuth-7.93° to 97.93°

. .

-7.93° to 97.93°

Azimuth

E1

E2 E4

E5 E6

E7

E8

E9

E10

E11

E12

362.75

362.75

Position Elevation degrees

E1 21.09 to -7.85

E2 21.09 to -7.85

E3 -7.93 to 26.15

E4 21.09 to -7.85

E5 -21.09 to 7.85

E6 -7.93 to 26.15

E7 21.09 to -7.85

E8 -21.09 to 7.85

E9 -7.93 to 26.15

E10 -21.09 to 7.85

E11 -21.09 to 7.85

E12 -7.93 to 26.15

Pointing stability (note 2)

Slew rate Max 18.0 deg / min and Min 2.0 deg / min

Max full range actuation time

17 mins


• Note 1: Accuracy error shall include but not be limited to pointing stability requirements, see note 2.


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• Note 2: Pointing stability must include the effects of, thermal distortion, backlash, hysteresis effects, composite dry-out, dynamic excitation caused by ion thruster operation, harness + pipework friction/resistance, and MLI.

Accuracy error shall include misalignment of the TPM axis with respect to given reference frame.

3.2.13.1 Re-establish a reference position

TPA-2604/CREATED/A,R

In a worst case it shall be possible to re-establish the reference position orientation for the thruster pointing.

3.2.13.2 Parasitic translation


Parasitic translation of the thrust vector during TPM operation shall be minimised, and reported to the Customer in the form of a matrix.

3.2.14 Unpowered Holding Torque


Backdriving of the Actuators shall not occur during worst case loading as described in TPA-434.

TPA-250//

The TPA shall be designed to function within the constraints of the GDIR (AD1)

3.3 Physical Characteristics

3.3.1 Mass Properties


• The total mass of each TPM shall be < 8.5Kg; the overall TPE mass shall be <2 kg, including all TPM harnesses and switches.

• The overall total TPA mass for 4 TPMs, all corresponding TPE's, harnesses and switches shall be <36 kg.

• The Contractor shall provide separately the calculated mass value, calculated C of G about the principle axis and inertia's.

• Upon its delivery the weighed mass, measured C of G about the reference axis shall be supplied.

• TPM includes hold-down and release mechanisms.

• The unit centre of gravity shall be measured with an accuracy of ± 1mm (TBC).

• The unit moment of inertia shall be calculated with an accuracy of ± 5% (TBC).

3.3.2 Equipments supported by the TPM


The following equipments are to be supported by the TPM and shall be considered for mass and Interface control implications:-MLI enclosure, Thruster, thruster harness, splice plate/hot interface, thruster pipework, connectors.

TPA-2969//

Worst case thruster mechanical characteristics shall be used.

Combined pipework and harness mass would be up to 1 kg/m (TBC).

Thuster mass 7.5 kg.

Mass of MLI 0.87 kg/m2 TBC.


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Xenon pipework is 1/8 inch Titanium tube.

Thruster Cof G X=0, Y=0, Z= 162.9mm + Thermal spacer 20 mm(TBC) above mounting face.

MOI Ix= 97396, Iy= 97396, Iz= 117034 kg.mm2 (TBC)

3.4 Interface Requirements

3.4.1 Electrical interface description

3.4.1.1 TPE to MCU Electrical connection

TPA-2966//

TBD

3.4.1.2 Power Supply

TPA-270/GDIR derived/T,A

The power required to operate the TPA according to the interface requirements in the GDIR will be 28V +1% / -3%supply within the MCU.

3.4.1.3 Telemetry and Telecommand Interfaces

TPA-2756/GDI-445 Derived/T,A,R

The discrete telecommand/telemetry equipment shall meet the requirements defined in GDIR GDI-445

Also see GDIR for wiring definition.


The TPE shall provide suitable redundant interfaces for at least the following discrete telemetry/telecommand

Purpose Type Flow Quantity Total number per S/C

Step commands for mechanism

Telecommand Standard Balanced Digital Link

MCU-TPE 1 + 1 per TPE 8

TPA motor/gearbox temperature monitoring thermistor

Telemetry TPE-MCU 1 + 1 per actuator 16

Positional data from the position sensing device

Telemetry

Standard Balanced Digital Link

TPE-MCU 2 per TPM 8

Limit switch status telemetry

Telemetry

Relay / Switch Status Acquisition Interface

TPE-MCU Redundancy and as required

TBD

3.4.1.4 Hold down and release mechanism electrical Interfaces

TPA-807/GDI-568 Derived/T,A,I,R

The HDRM electrical interfaces shall be as defined in the GDIR para 3.6.3 (GDI-568).


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Purpose Type Flow Quantity Total number per S/C

For information only

HDRM release Pyro firing pulse PCDU-TPM as required per TPM

as required Pyro/NEA firing pulse

3.4.1.5 TPM to TPE Harness

TPA-2920//

The harness between the TPM and TPE shall be split near the base of each TPM. Fixed connectors shall be provided on the TPM to allow for disconnection of the TPE harness. This is required for integration and test of the TPM. See also TPA-374

TPA-791/CREATED/A,I

TPM to TPE (MCU) harness lengths are as shown in TPA-2817. These distances are only a guide and approximate. TPEs should be able to drive the TPMs with any interconnecting harness length up to 5m.

TPA-2817/CREATED/A,I

MEPS THRUSTER # LENGTH TO MCU IN mm COMMENTS

MEPS Thruster 01 2129 Approx. 50mm radius assumed (TBC)




0 1

0 2

0 3

0 4

M C U

0 1

0 2

0 3

0 4

M C U

Figure 3.4-1: TPM to TPE(MCU) harness routing and length

3.4.1.6 Thruster harness.

TPA-1151//

The SEPS harness between the PPU and thruster/FCU shall be split near the base of each TPM. Connectors (or equivalent) shall be provided to allow for disconnection of the thrusters or connection to simulators for spacecraft level ground tests and reconnection to the thrusters for flight. see also TPA-374, and TPA-2969

3.4.1.7 Wire Harness

TPA-303/GDI-570 Derived/I,R

All cabling, cable routing, labelling and connectors shall be in accordance with the GDIR GDI-570 (AD1) and to the requirements of EICD. See also TPA-2817

TPA-1104/GRIR Derived

/T,A,I

Metallic shells/receptacles of connectors shall be electrically bonded to the equipment case. The equipment shall meet the requirements (see GDIR) for power and signal grounding.


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3.4.2 Mechanical Interface


The TPE boards that are housed in the MCU shall have maximum dimensions of 260 x 270mm

TPA-372/CREATED/A,R

The interface requirements for the TPM are specified in 3D models. These requirements are critical to ensuring the thruster clears the spacecraft constraints (structure and field of views) during deployment and test.


3D Models DT0285635-01 and DT0285634-01 will be provided by Customer.

Model DT0285635-01show the TPM/Thruster stowed stay out volume including the LVA structure perimeter limitations prior to LVA separation. For TPM pointing this perimeter limitation will be removed as the LVA will have separated.

Stay out zone for TPM installationStay out zone for TPM installation

Figure 3.4-2: TPM deployed stay out volume 3D model DT0285635-01

Model DT0285634-01 shows the allowable volume for the TPM/Thruster in its launch position prior to LVA release, typical 4 positions.


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Thruster stowed volume

TPM stowed volume

Thruster stowed volume

TPM stowed volume

Figure 3.4-3: TPM/Thruster in its launch position prior to LVA release. 3D model DT0285634-01

TPA-2917/CREATED/A,I

The TPM interface with the Thruster shall be in accordance with thruster described in TPA-2969 This is a worst case between the RIT22 Thruster IZ_1131711(Draft), and the QinetiQ T6 Thruster CS030006911(Draft).

3.4.3 MCS Physical Reference Frame

TPA-251//

The TPM shall provide a reference frame (axis set) that can be clearly related to the Spacecraft axis and repeatable on the hardware.

TPA-2608/MPB-4043/A,R

The MCS co-ordinate system shall be as defined in [TPA-2609].

The +Y axis is nominally sun-pointing.


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TPA-2609//

MMO

MTMMCS

LVA

+z

+x+y

+x

+z

+y

+z

+x+y

MOSIF

+x+y

MPO

+x+y

+z

+z

+x+y

+z

FREGAT

MMT / MPOseparation plane

FREGATmounting plane

Main Coordinate System

MPO / MOSIFseparation plane

MMOseparation plane

LVA / MTMseparation plane+z

+x+y

MCS incl. LVA

SEM (145mm)

Figure 3.4-4: MCS co-ordinate system

3.4.4 Interchangeability

TPA-443/GDI -69 Derived/I

All 4 TPMs shall be identical and interchangeable. There shall be no matching of individual TPE and TPM which will result in loss of interchangeability.

TPA-1114/GDI -69 Derived/I

The equipment must be of the same qualification status and reliability to meet interchangeability requirements.

3.5 Performance Requirements

3.5.1 TPM Pre-release Stiffness


The TPM will be analysed and tested with thruster mass and inertia dummy described in Para 3.2.1 The TPM assembly (TPM, thruster dummy, harness, pipework, and MLI assembled) shall satisfy the following stiffness requirements under launch load in a launch load configuration:


TPM 1st lateral (X and Y S/C axis) resonant frequency 70-80 Hz.

TPM 1st vertical (Z S/C axis) resonant frequency 70-80 Hz.

3.5.2 TPM Post-Release fundamental frequency.


The fundamental frequency of the TPM (X,Yand Z S/C axis) will be >2.5Hz (TBC) after release of HDRM, including a mounted thruster.


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3.5.3 TPE fundamental frequency


The fundamental frequency of the TPE shall be.

TPE 1st lateral and vertical resonant frequency > 150 Hz.

3.5.4 Reliability

TPA-338/CREATED/A,R

The TPA End of Life reliability shall be calculated and reported by the Contractor.

TPA-2605/CREATED/A

The failure mode effects and their criticality shall be taken into account when demonstrating the design fault tolerance. Special account shall be taken of electrical and thermal failure propagation within the actuators.

TPA-360/PARS-Derived /A,R

Redundancy concepts shall be selected to minimise single points of failure and to optimise reliability for the mission and life requirements. Where a single point failure mode is identified and cannot be made redundant, the required reliability shall be demonstrated. Single point failures shall be avoided where ever possible and shall be reported as a critical item in the critical items list. AD-18 applies.

See also AD 01 Para 3.1.3

3.5.5 Lubrication

TPA-382/GDIR- Derived/T,A,I,R

Lubrication shall be guaranteed in ground test and flight temperature environment. If not, it shall be demonstrated that the lubrication is effective during a duration of 2.0 times the flight operation mission plus ground operations, including the loss of lubricant due to operation in a vacuum, also GDIR AD 01


Maximum period without maintenance shall be specified

3.5.6 Outgassing

TPA-383/PARS-Derived/A,R

Outgassing shall comply with the requirements of AD18

3.5.7 Fatigue

TPA-550/MPB-3584/A,R

The Contractor shall consider the following for sources of fatigue in the design of the TPM for all models.

• Ground testing and transportation

• Vibration test levels at TPM level

• Vibration tests at Spacecraft level

• In Orbit thermal cycling and power cycling effects

• Fatigue analysis shall demonstrate a positive MOS after application of 4 times the most demanding life cycles. Effects of stress concentrations shall be taken into account.

• The Contractor is responsible for Fatigue analysis and reporting.


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3.5.8 Corrosion of Materials


Stress Corrosion Sensitivity shall comply with the requirements of AD18


Corrosion Resistance Shall comply with the requirements of AD18

3.5.9 Dissimilar Metals

TPA-1118/PARS-Derived/A,I

Contact of dissimilar metals with each other shall be avoided wherever possible. Protection against electrolytic corrosion which can result from such contact shall be provided by surface treatment of the metals. Dissimilar metal contact shall be approved by Astrium satellites. see AD 18

3.5.10 Output Torque


Each TPM shall provide an output torque to enable it to overcome the resistive torque, and inertial loads identified in this document

TPA-429/GDI-185 Derived/A,R

Safety factors shall be applied, in the torque margin budget, on all the torques internal and external to the actuators - see (AD1) Para 3.2.1.6.2 GDI-185.

3.5.11 Testing in 1G Environment


The TPM shall be designed to be released and to subsequently point the thruster and its supporting structure in a 1G environment in any orientation without degradation (this assumes testing mounted on a vertical S/C). Any pointing error during this operation shall be quantified by the Contractor.

If this causes a problem such as motion creep, inadequate torque margin, etc. then the aid of a non flight off load device during ground testing is allowed by agreement with the Customer, and the TPM must have the facility for applying this.

The Contractor shall identify any additional precautions to be taken for release and movement under 1G conditions resulting from this requirement, and to supply associated MGSE.

3.5.12 Structural Requirements


The unit shall be designed to withstand the environments it will encounter during its lifetime without degradation of its performance, and without detrimental influence on the spacecraft or any other unit. The following shall be taken into account:

• fabrication and assembly loads,

• handling and transportation loads,

• test loads (including thermal stresses),

• launch loads (vibration including shock, thermal and depressurisation),

• operational loads,

• Structural dimensioning of the unit shall consider critical combination of simultaneously acting loads.


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3.5.13 Structural Analysis

TPA-557/MPB-3573/T,A,R

MPB is responsible for overall MTM mechanical coupled analyses.

Margin shall be in accordance with GDIR GDI-185

The Contractor is responsible for SEPS pipework and harness mechanical and fatigue analysis, as detailed in Annex J of SOW (BC-ASU-SW-00001)

TPA contractor will be responsible for mechanical analysis of the TPM, assuming the MTM structure is a rigid interface.

The structural analysis shall be performed on all parts of the TPA. The analysis shall cover ground operation, launch loads, and cruise. Random, quasi-static, sine and fatigue analyses shall be performed to verify all structural margins are met. Thermal stress and distortion analyses shall be performed to ensure that the TPA can sustain the predicted temperatures and behave within the specified dimensional requirements over the qualification range. Structural analysis shall be supported by finite element modelling (FEM) of the TPA. MSC/Nastran shall be used for FEM analysis. Structural models shall be supplied to assist the thruster subsystem analysis. Nastran with a numbering range for a single TPM should be 350,000 to 359,999 (a range of 10000) applicable for all entities (e.g. Nodes, Elements, Materials, Properties, Co-ordinate systems). Ref AD11

3.5.14 Isolation

TPA-308/GDI-2240 Derived/T,A,I

The equipment shall comply with GDI-2240

3.5.15 Grounding and Bonding.

TPA-305/GDI-2242 Derived/T,A,I

The equipment shall comply with GDI-2242

3.5.16 EMC Environment

TPA-279/EMC Derived/T,A,R

The TPA shall be electromagnetically compatible, both internally (intrasystem) and with the spacecraft, test, pre-launch, launch and operational environments (intersystem). This shall be achieved by demonstrating compliance as applicable with the following requirements. The performance characteristics of the TPM shall be maintained during EMC testing.

3.5.17 EMC Performance Requirements

3.5.17.1 Inrush Current


The equipment shall comply with AD 03 paragraph 5.1.1

3.5.17.2 Voltage Transients.


The equipment shall comply with AD 03 paragraph 5.1.2

3.5.17.3 Conducted Emissions


The equipment shall comply with AD 03 paragraph 5.2


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3.5.17.4 Radiated Emissions


The equipment shall comply with AD 03 paragraph 5.5 and 5.6

3.5.17.5 Radiated Susceptibility


The equipment shall comply with AD 03 paragraph 5.7 and 5.8

3.5.17.6 Conducted Susceptibility



3.5.17.7 DC Magnetic Requirements



3.5.17.8 ESD Susceptibility



3.5.18 Radiation Environment

TPA-2476/ET Derived/T,A,R

Materials and components shall be selected to ensure the equipment meets the requirements of this specification when subjected to the conditions defined in (AD-02 para 6).

3.5.19 Margins of Safety

TPA-478/MPB-3579/T,A,R

Strength analysis shall demonstrate positive margins of safety against yield, ultimate and buckling loads where applicable for all the components. AD 1 Para 3.2.1.6.2 GDI-185 shall apply.

3.5.20 Resistive torque


The harness and pipework set associated with each thruster will present resistance torque(TBA by contractor), when subjected to rotation of the thruster (on its gimbal) over the range identified in this document, with the FCU and PPU hard mounted to the spacecraft structure. A harness containing 22 x 20AWG shielded high voltage cables shall be considered, and 3 Xenon 1/8 inch Titanium pipes. Additional MLI stiffness of 3 Nm (TBC) shall also be taken into account. The TPA shall provide sufficient net actuation force to operate against the total resistive torque. Total resistive torque excludes TPA itself.


The SEPS pipework and harness shall be attached to the thruster at its side. There shall be no requirement to route either the pipework or harness through the base of the thruster (i.e. through the face mounted to the TPM).

TPA-517/GDIR Derived/T,A,R

The design of components shall be sized to provide actuation margins in accordance with the GDI-2185

3.5.21 Factors of safety

TPA-2421/GDIR Derived/T,A,R

The factors of safety shall be applied to the qualification loads to compute the margins of safety.


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The equipment shall comply with AD 1

3.5.22 Thermal Performance Requirements

3.5.22.1 Radiative Thermal Interface

The TPMs are fully enclosed within the MTM engine bay: an MLI blanket located at the level of the TPM to SEPT interface ensures that there is no direct view between the TPMs and the SEPTs and the MTM main engine. In addition, this means that the TPMs do not have a direct view to space (for cooling purposes, for example). However, they never see any solar flux, either. Within the engine bay, a dedicated heat shield covers the hot parts of the main engine (see TPA-2814 ).

See also TPA-786 for interface operating temperatures plus margin

The MTM structure within the engine bay is also covered with MLI.

This MLI is supplied by the Customer via the MLI contractor, and configuration to be shown in ICD (TBC).

The Customer shall provide the engine bay geometry. See TPA-3032

Outer HT MLI covering

engine bay

VDA-covered

engine bay sides

Main Engine Heat Shield

TPMs - presently bare metal finish (no MLI is TBC)

VDA-covered

engine bay floor

The view on the right shows the TPMs with the engine bay MLI removed. The need for additional MLI directly on the mechanisms themselves is currently not foreseen, but remains TBC at this stage.

Areas for TPM spec TO Props

Pyramid 1.7m² VDA e=0.05

ME shield 1.4 m² Titanium e=0.25

Bott Flr MLI 1.8 m² VDA e=0.05

Outer MLI 1.8 m² VDA e=0.05

TPM - Aluminium (TBC)


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The TPM thermal design, undertaken by the Contractor, shall take into account the following radiative environment parameters in TPA-2961, TPA-2962 and TPA-3049


Engine Bay MLI:

Emissivity: 0.05

Main Engine Heat Shield:

Emissivity: 0.25


The radiative environment temperature range that shall be considered for the MTM engine bay is -125 to +70°C (TBC).


The TPM shall withstand a dissipation from the SEPS harness of up to 2W/m (TBC)

3.5.22.2 Interface surfaces:

The Mechanism will be thermally isolated from the SEPT as far as possible. The coupling per thruster is expected to be on the order of 0.06W/K TBC.

TPA-758/CREATED/A,R

Conduction to and from the satellite is to be agreed with the Customer in order to optimise thermal control of mechanism without placing the thermal control of the satellite at risk. Each TPM shall not rely on conducting more than 10W (TBC) to the spacecraft (MTM) structure for its thermal control.

3.5.22.3 Thermo-elastic Analysis


The Contractor shall perform the detailed thermo-elastic analysis of the TPA based on the worst case thermal environments. The TPM is bolted to a honeycomb panel.

3.5.22.4 Thermal Mathematical Model Requirements

TPA-559/GDIR Derived

CREATED/A,R

The Contractor shall substantiate the thermo-optical properties and the conductive couplings used in his model.

The Contractor shall define his thermal model using the MTM co-ordinate system in TPA-2608

The Contractor shall use node numbers in the range 42100 - 42499.

The Contractor shall provide a reduced thermal model in ESARAD/ESATAN format as input to the MTM thermal model

The detailed thermal model of a unit shall be verified and correlated with a thermal test in accordance with the GDIR GDI-335, GDI-338 and GDI-340.

3.5.22.5 Heat Flow

TPA-567/CREATED/A,R

The conductive coupling between each TPM and the MTM is 0.5 W/K (TBC) and the interface temperature range is specified in para 3.6.1


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3.5.22.6 Thermal Control


The Spacecraft will guarantee the specified thermal environment, but the TPA supplier is responsible for the thermal design and control required to keep components in their required temperature range within this environment. Any resulting heaters and thermostats, including redundancy are to be provided as part of TPA, and power from the TPEs. This internal thermal control shall be self-contained, and not rely on any hardware or software from the spacecraft

TPA-1088/CREATED/T,S

Where a specific finish is selected (e.g. a paint), it shall be demonstrated that this is compatible with the range of conditions experienced over the complete BepiColombo mission.

TPA-247/CREATED /R

MLI thermal blankets will be the responsibility of the Customer.

The TPM interface to the thruster shall be capable of accommodating MLI attachments (e.g. standard blanket studs).

The Customer shall define the location of the MLI attachments.

TPA-1091/CREATED/A

The TPA units shall allow for the attachment of thermal monitoring devices on at least the thruster mounting interface

3.5.22.7 Thermal Control Elements

TPA-796/CREATED/A,R

The TPM contractor shall provide, if necessary, heaters (Prime and redundant) to maintain the temperature of any sensitive components within operational temperature range.

3.5.22.7.1 Heaters

TPA-801/CREATED/A

If heaters are required for specific control of TPM elements, their position and type shall be reported to the Customer. See TPA-569

3.5.22.7.2 Thermistors

TPA-803/CREATED /A

The TPA contractor shall provide Thermistors for temperature monitoring of the motor/gearbox assemblies.

3.5.22.7.3 Thermostats

TPA-805/CREATED/A

Safety cut out thermostats shall be provided in the heater circuits.

3.5.23 Life

TPA-2422/MPB Derived/T,A,I,R

Life test to be performed reference ECSS-E-30 Part 3

The purpose of the life test model is to prove by testing that the mechanism can perform the required quantity of cycles under extreme conditions, taking into account the applicable margins. For development schedule or development risk reduction, this model can be a specific model.

TPA-343/MPB-4555/T,A,I,R

The design shall allow for at least the following cycles on each actuator with a steering angle varying from zero to the full pointing range in 2 orthogonal axes:


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The Thruster Pointing mechanism shall be qualified considering the following in-flight movements and characteristics with related elements (e.g. piping and harness, MLI) in place:

• number of large slews ≥ +/- Full range: 3000 (including on ground cycles)

• number of slews ≥ +/- 5°: 3000 (including on ground cycles)

• small increments of +/- 0.1°: 170000 evenly distributed over a pointing range of 2.2° (TBC) from a start position to be supplied by Customer based on proposed design.

• number of slews to reference / end stops: TBD


The rotations may be around any point, but will be within the overall angular range specified.


Following periods of TPM “dither” (very small pointing movements), it may be possible to perform exercising if absolutely necessary, and kept to a minimum (to be defined by the Contractor and shall be agreed by the Customer before implementation).

TPA-351/MPB Derived/A

The specified performance of the TPA shall be maintained without degradation for 6.6 years of mission life of the satellite.

TPA-352/GDI Derived/A

Furthermore, and in addition to this, there shall be a maximum on ground lifetime / storage period that will not exceed, after delivery:

• 5 years in a standard clean room environment. (Class 100,000)

• 2 years in a storage environment.

TPA-355/MPB Derived/A,I

Maintenance during storage and long periods of non operation during flight shall be as limited as possible and, if required, shall be identified by the Contractor for approval by the Customer.

TPA-356/MPB Derived/T,A,R

• The pre-loaded HDRM shall be compatible with a release operation up to 3 months after assembly (ground) and 2 months after launch (total 12 months).


• HDRM (excluding NEA) shall be capable of 50 releases. The need for periodic refurbishment shall be identified by contractor.

TPA-357/MPB Derived/T,A,R

• The TPA performance shall be met throughout the thruster pointing assembly lifetime. Lifetime is understood to include on ground, storage, launch and all mission phases.

TPA-358/MPB Derived/I

• The Contractor shall record the number of on ground deployment and trimming operations which shall be supplied to the Customer. This shall be recorded as motor revolutions (in and out of vacuum), and angle moved.

TPA-359/CREATED/I

• A record shall be maintained for the number of HDRM releases


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3.5.24 Protective Functions

TPA-277/CREATED/A

Protective functions (temperature control and stall current limitation) needs to be implemented independently of the nominal control functions such that no single failure results in loss of control and protection

3.5.25 EEE Parts

TPA-310/PARS Derived/I,R

AD 18 section 7 shall apply.

3.5.26 Single Event Effects (SEE)

TPA-682/ET Derived/T,A,R

The equipment shall comply with TPA-2476 Radiation Environment

3.5.27 Thermal Environments

The Customer is responsible for overall MTM thermal coupled analyses.

The concept is to thermally isolate the SEP thruster as far as possible from the rest of the spacecraft.

Specific issues include the thermal control of the SEPT/ TPM assembly.

The SEPT is expected to radiate dissipated heat directly and be thermally isolated from the TPM. A flexible blanket is anticipated around the TPM, with a limited heat flow at the TPM to MTM structure interface for thermal control.

3.5.27.1 Temperature Margins and Limits


The TPA units shall be subjected to the following during thermal testing.

Test Parameter Qualification PFM Acceptance

Temperature margins See requirement See requirement See requirement

Vacuum/Balance * 10-5 Torr 10-5 Torr 10-5 Torr

Vacuum Cycles 8 4 4

Max rate of change 2°C/min 2°C/min 2°C/min

* thermal equilibrium when a rate of less than 1°C/hr for at least 1 hr is achieved

3.5.28 Actuator Backlash

TPA-3035//

Actuator backlash shall be zero.

3.5.29 Optical alignment cube.

TPA-3039//

The TPM thruster mobile plate shall accommodate an optical cube to align the TPM on assembly to S/C and subsequent verification activities.

3.5.30 Failure Tolerance

TPA-3028//

The failure tolerance requirements of GDIR-AD 01apply as listed in the GDIR Applicability Matrix provided in Section 7. The GDIR requirements GDI-3136 , GDI-3119, GDI-3123 cannot be used on equipment level and they are applicable as derived below.


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TPA-3024/GDIR 3136 Derived/A

The design of units with embedded redundancy shall be such that that a single component/part failure (e.g. resistor, transistor) cannot, as far as practicable, cause the failure of any function of the equipment. Single point failures which cannot be eliminated from the design with reasonable effort (or fault tolerance requirements which cannot be met) shall be summarised in a Single Point Failure/Critical Items List. They are subject to formal approval by the customer up to prime contractor on a case by case basis with a detailed retention rationale.


The contractor shall verify the capability of the design to sustain single failure as defined by the following failure tolerance requirement.

• No single hardwarehardware failure or operator error shall cause effects on equipment functions of the dependability severity category 1 (Propogation of failure to other subsystem/assembly/equipment) and - for units with embedded redundancy only- level 2 (Loss of functionality). Single Point Failures which cannot be eliminated from the design with reasonable effort (or fault tolerance requirements which cannot be met) shall be summarised in a Singlr Point Failure/Critical Items List. They are subject to formal approval by the customer up to prime contractor on a case by case basis with a detailed retention rationale.


Any command or command sequence that can cause

• Consequences of the hazard severity category 1 (Catastrophic - Loss of human life; life threatning, permanently disabling injury or occupational illness) or

• dependability severity category 1 ( Propogation of failure to other subsystem/assembly/equipment) or-

• for units with embedded redundancy onlu- level 2 (Loss of functionality ) or

• cause damage to flight hardware if issued inadvertantly or not issued when required (out of sequence commanding) shall be identified in the FMECA and reported in the Hazard Analysis.

3.6 Environmental Conditions

TPA-571//

The TPA shall be capable of withstanding test, launch, cruise and orbital environments as specified herein without failure, malfunction, or degradation in performance.

3.6.1 Thermal environment (Extreme temperatures and maximal thermal gradients)

TPA-2695//

The Customer ensures that the TPM interfaces see the temperature ranges specified in TPA-786. The Contractor is responsible for the thermal design internal to the TPM.

This includes the thermal hardware required in TPA-803 & TPA-805.


Max gradient based upon worst case interface operating temperatures plus margin: spacecraft interface temp: -50 deg C (min), 65 deg C (max) SEPT interface temps: qual range +200 deg C (max), -60 deg C (min). Deployed and stowed.

Concept is to thermally isolate thrusters from mechanism but implement a degree of conductivity across mechanism to spacecraft interface.


Based on the current thermal modelling performed by Astrium Ltd the required temperature limits for all the TPM components are as follows,


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Lower / Upper Operating Design Limits = -40/+100°C

Lower / Upper Operating Acceptance Limit = -50/+115°C (TBC)

Lower / Upper Operating Qualification Limit = -60/+130°C (TBC)

See also para 3.5.22.

TPA-2916/ET-14757/T,A,R

Based on the current thermal modelling performed by Astrium Ltd the required TPE interface temperature limits are as follows.

Operating Design Limits are -30°C to + 65°C (TBC)

Operating Acceptance Limits are -35°C to + 70°C(TBC)

Operating Qualification Limits are -40°C to + 75°C(TBC)

TPA-2970//

The Modalities of heat exchage with the MCU (conduction with baseplate, radiation with chassis and other boards) are TBD.

3.6.2 Vibration Environments

TPA-574//

The TPM shall be powered off and Launch locked during all vibration and mechanical static load tests. The TPM shall be rigidly fixed at the Spacecraft interface and shall have a representative mass/inertia at the thruster interface. STM, and EQM are subjected to qualification levels for qual duration. See AD1.

The thrusters and pointing mechanism shall be compatible with the following mechanical loads when launch locked.

The TPM interface loads defined from the quasi-static load case, sine, random, shock and thermal environments shall satisfy no slippage or gapping at the bolted interfaces.

3.6.2.1 Quasi-Static TPM Input (at the base of the TPM)


All TPM models shall be tested with thruster mass and inertia simulated (Thruster mass 7.5kg TBC. For Cof G and MOI see TPA 2969) and has to withstand, without any degradation, the loads induced by test as follows:

TPA-580//

• 30G (qual.) quasi-static, all directions

3.6.2.2 Sine TPM Input (at the base of the TPM)


12G (qual.) sine from 5 to 100Hz. TBC


Any notching is a waiver to the requirement and as such shall be justified by a detailed analysis and submitted to Astrium for approval a week in advance of the review/test date.


During sinusoidal excitation, equivalent quasi-static loads are defined as the algebraic sum of interface forces divided by total mass. Input levels may be notched to prevent these equivalent quasi-static loads exceeding the specified quasi-static levels on each axis. The Contractor is allowed to propose other criterion.


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Qualification level = Acceptance level x 1.5


Acceptance sweep rate shall be 4 oct/min.


Qualification sweep rate shall be 2 oct/min.

3.6.2.3 Random TPM Input (at the base of the TPM)


The Random qualification test levels shall be as shown in Table 3.6-1 (TBC) Where M Mass of TPM + thruster


Table 3.6-1: Random qualification test level and duration (Ref ECSS E 10 03A p.58)

3.6.2.4 Shock Requirement TPM Input (at the base of the TPM)


The TPA assembly shall be rigidly fixed at the Spacecraft interface and shall have a representative mass/inertia at the thruster interface, and shall be designed to withstand the shock environment in Figure 3.6-1 for a total of 3 shocks applied independently in each of the 3 orthogonal axes.


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Figure 3.6-1: Shock environment

TBC

3.6.2.4.1 Vibration and Shock Levels at Thruster Interface


The loads at the Gimbal plate to thruster interface shall not exceed the following, when the TPM is exposed to the levels identified in TPA 582, 1826, 596 in order to protect the thruster.


Frequency (Hz) Peak Level

5 - 100 ± 10mm 0 to peak

38g

Table 3.6-2: Sine

TBC


Random (qual): As per table

Table 3.6-3: Random

TBC


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Frequency (Hz)

Level (g2/Hz)

Slope (dB/Oct)

10 0.0236 -

10 to 70 - 6

70 to 200 1 -

200 to 215 - -29

215 to 455 0.5 -

455 to 2000 - -6

2000 0.026 -


Shock: As per table

Frequency (Hz) Acceleration (g) perpendicular

Acceleration (g)

parallel

100 10

200 30

3000 2000 3000

10000 2000 3000

Table 3.6-4: Shock

TBC


The TPM must be compatible with a Thruster first eigen frequency of > 100 Hz to reduce potential amplifications. See also TPA-546

3.6.2.4.2 TPE (MCU) Input

3.6.2.4.2.1 Quasi-static

TPA-2932//

40G (qual) for all directions TBC

3.6.2.4.2.2 Sine

TPA-2934//

20G (qual) in any direction TBC

3.6.2.4.2.3 Random

TPA-2936//

+3dB/Oct to 60Hz, 1.5G^2/Hz from 60 to 400Hz, Then -3dB/Oct to 2000Hz (qual) TBC

3.6.2.4.2.4 Shock

TPA-2938//

TBD


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4 PRODUCT ASSURANCE REQUIREMENTS

4.1 Project Quality

TPA-362/PARS Derived/A,R

AD 18 (and AD 09) shall apply. Those requirements of AD 18 (and AD 09) particular to the product shall be reflected in the contractors PA Plan.

All products supplied against this specification shall be as safe as reasonably possible, and assessed in accordance with ECSS-Q-40B. It shall be supplied with documentation addressing safety & EMC risks. Safety warning labels are to be attached as appropriate.

Note - AD 09 only applies if the equipment will have software

4.2 Storage

TPA-866/GDI-35 Derived/A,I

The container shall guarantee the integrity of the TPA units, 5 years after the delivery date without repairing or refurbishment. See GDIR AD1(GDI-35)


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5 GSE REQUIREMENTS

5.1 Ground Handling

TPA-852/GDIR Derived/T,A,I

The design of GSE shall be such that risks to human health and safety are minimised as far as reasonably possible.

All GSE will be assessed, by the contractor, for compliance with European legislation. If applicable, a Declaration of Conformity shall be supplied to the Customer and the

GSE shall be CE marked. This requirement is applicable irrespective of the site upon which the GSE is to be used.


The Contractor shall supply a test unit to drive the TPA to meet the requirements of this specification, and a unit suitable for HDRM release. The GSE shall enable operation of the TPMs directly, or via the TPE.

The Customer shall supply an ICD of the local spacecresft structure to enable the Contractor to supply suitable MGSE ( if required ) for spacecraft level intergration.


Provision to be made for fixing thruster protection guards. TBC

5.2 Transportability

TPA-857/GDI-75 Derived/T,A

See GDI-75 AD1

TPA-248//

The Contractor shall also be responsible for the provision of the operating manual(s), shipping containers, MGSE, EGSE and any other equipment required to test and transport the TPA.

TPA-249//

Each TPM shall be delivered to the Customer in a fully assembled and tested condition and locked in flight configuration, unless not recommended by the Contractor to meet transportation requirements


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6 VERIFICATION REQUIREMENTS

6.1 Surveillance, and Witness of Inspection and Test

TPA-1155//

The Customer shall be given access to the Contractors facilities at all times in order to inspect the Contractors quality control system and the records specified to be maintained therein. The Contractor shall assure that appropriate arrangements are made for access to lower tier Vendor's facilities/test houses where critical operations are to be performed.

TPA-1156//

The Customer (or their nominated representatives) reserve the right to witness, perform, or review the tests or documentation of any of the inspections set forth in the specification where such inspections are deemed necessary to assure that supplies and services conform to prescribed requirements.

TPA-1157//

The Contractor shall notify the Customer at least 2 weeks and subsequently 48 hours prior to the commencement of the qualification or acceptance test phases to enable representation by the Customer and witnessing of any or all tests as considered necessary by the Customer.

6.2 Cleanliness Requirements

TPA-2647/PARS Derived/A

Cleanliness requirements in accordance with AD-01 & AD-18 shall apply.

6.3 Verification Matrix

TPA-870//

The Contractor shall propose as part of their technical proposal a verification matrix to cover all the specified requirements. The verification method shall be defined e.g. Design, Analysis, Test, Heritage, etc.

The method of verification of all paras of Section 2, Section 3, and Section 6 of this specification shall be presented in a Design Verification Matrix Report.

In addition, early confidence testing activities should be performed: - Transfer function needs to be validated at an early stage e.g. Electric thruster pipework and harness fatigue under TPM motions life cycle. - Life cycling of TPM actuators.

6.4 Test Requirements

TPA-871/CREATED/T,A,I

The contractor shall meet the following verification and test requirements as a minimum. However, these requirements should not necessarily be considered as exhaustive, and the contractor shall also include additional tests as necessary to demonstrate complete compliance of the TPA with the requirements stated.

TEST EM EQM

QM

PFM FM

Electrical Interfaces PT PT PT


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TEST EM EQM

QM

PFM FM

Functional / Performance Tests (4)

-motor winding resistance and inductance

-insulation / isolation

-motor start current

-motor running torque

-motor detent torque

-motor torque wave form

-motor back EMF characteristics

-dielectric strength

-number of steps per turn

-output torque verses current or voltage and command frequency.

-linearity

-torsional stiffness

-torsional stiffness linearity

-back drivability

-resistive torque at ambient

-run-out

-output shaft stiffness

-gearbox efficiency verses temperature, speed and output load

-gearbox backlash

-actuator assembly resolution

-actuator assembly output torque verses current or voltage, command frequency, temperature, speed and output load.

-output step angle

-drive ratio

-rotation range

-step rate

-holding torque (powered and un-powered)

-positional accuracy

-power consumption

PT PT PT PT

Position sensing devices

-calibrate angular accuracy and linearity

PT PT PT PT


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TEST EM EQM

QM

PFM FM

TPA

-axial, translational, and torsional stiffness

-position error

-run out

-power dissipation

-electrical noise

PT PT PT PT

Life test (3)

QT

Software tests, including hardware/software interface

(if applicable)

PT PT PT PT

Mechanical Tests

- Mass, Dimensions, Interfaces, CoG, MoI QT PT PT PT

- Shock test QT QT QAT

- Sine Vibration QT QT QAT

- Random vibration (or Acoustic, if more representative)

QT QT QAT AT

Thermal Tests

- Thermal Vacuum QT QT QAT AT

EMC Tests

- Bonding T T T T

- Primary Power Isolation T T T T

- Power quality (inrush current) T T T

- Magnetic Moment T T 1)

- Conducted Emission, Frequency domain T T T T

- Conducted Emission, transients T T T

- Conducted Emission, secondary power lines T T 1)

- Conducted Susceptibility, frequency domain T T 1)

- Conducted Susceptibility, Transients T T

- Conducted Susceptibility, secondary power lines T T 1)

- Radiated Emission, Electrical field T T 2)

- Radiated Susceptibility, Electrical field T T

- ESD radiated T T


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Legend: PT: Performance Tests Vs: Verified by Similarity

T: Test 1) test only if design mod between EQM and (P)FM

QT: Test to Qualification Level 2) in case of critical notches

QAT: Qualification levels tests with acceptance duration

3) The life test shall be conducted at TPA or TPM level.

This life may also be required to include flight representative pipework and harnesses, to be provided by the customer

AT: Test to Acceptance Level 4) Functional and performance tests shall be performed at motor, motor/gearbox and TPA level as indicated

5) The qualification status of the position sensing device will be reviewed to assess any delta qualification needed.

6.5 Configuration and Data Management (CADM)

TPA-1055//

The TPM documentation shall conform to the general requirements set out in AD6.


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7 GDIR APPLICABILITY MATRIX

The following table lists the applicable requirements of the GDIR.

It contains, in the first column, the Local ID for each applicable GDIR requirement number.

The second column contains the GDIR Requirement number and the opening text of the requirement.

The third column defines the Applicability Y/N

The final column shows the intended verification method. If no method is shown it shall be assumed that verification is required and the method is TBD

Req No. Reference Applicability Verif. Method

2.1 Applicable Documents TPA-2834 GDI-3994:

The following documents, of the latest issue, or o ... Y

2.2 Applicable Standards TPA-2835 GDI-3993:

The following documents, of the latest issue, or o ... Y

2.2.1 ECSS 2.2.2 Military/Industrial TPA-2836 GDI-3287:

All BepiColombo documentation shall use the SI Int ... Y R

3.1.1 Lifetime TPA-1197 GDI-35:

The equipment/subsystem shall meet the requirement ... Y TBD

TPA-1198 GDI-38: Maintenance during storage shall be as limited as ...

Y A

TPA-1199 GDI-53: The MTM equipment/subsystems shall be designed wit ...

Y T,A

TPA-1200 GDI-48: Where the design margin on nominal lifetime is not ...

Y R,TBC

TPA-1201 GDI-49: The lifetime of items which degrade shall be desig ...

Y R,TBC

3.1.2 Safety and Product Liability TPA-1203 GDI-55:

The subcontractor shall comply to the applicable s ... Y A

TPA-1204 GDI-56: The subcontractor shall comply to the applicable p ...

Y A

TPA-2838 GDI-3137: Alternate or redundant paths shall be functionally ...

Y A

TPA-2839 GDI-3138: Checkout of all redundant paths and contingency op ...

Y A

TPA-2840 GDI-3118: The contractor shall verify the capability of the ...

Y A

TPA-2842 GDI-3120: No single hardware failure or operator error shall ...

Y A

TPA-2843 GDI-3121: No two hardware failures, two operator errors, a c ...

Y A

TPA-2844 GDI-3122: Improper command or command sequences or software ...

Y A

3.1.4 Venting TPA-1206 GDI-65:

Provisions shall be implemented in the design of t ... Y R

TPA-1207 GDI-66: The method of venting shall prevent the release of ...

Y R


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TPA-1208 GDI-59: The equipment/subsystem shall be able to operate w ...

Y A,R

TPA-1209 GDI-63: Vents shall be < 5mm diameter and > 1.5mm diameter ...

Y R

TPA-1210 GDI-60: For all relevant thermal hardware, explicitly MLI, ...

Y R

TPA-1212 GDI-62: Structural members (honeycomb panels, in particula ...

Y R

3.1.5 Interchangeability TPA-1214 GDI-70:

All spacecraft equipment/subsystems of the same pa ... Y R

3.1.6 Identification & Marking TPA-1216 GDI-72:

The equipment hardware shall be identified with a ... Y I

TPA-1217 GDI-73: The equipment/subsystem identification nameplate s ...

Y I

TPA-1218 GDI-74: For the particular case of connector identificatio ...

Y I

3.1.7 Accessibility/Maintainability & Ground Testing Requirements

TPA-1220 GDI-82: The design of the equipment/subsystem, the positio ...

Y R

TPA-1221 GDI-83: The equipment shall be designed to require a minim ...

Y R

TPA-1222 GDI-84: No field maintenance, servicing or adjustment shal ...

Y R

TPA-1224 GDI-87: Pyro or release mechanism or single shot device in ...

Y R

3.1.8 Transportation, Handling and Storage 3.1.8.1 Transport TPA-1227 GDI-77:

The equipment/subsystems shall be transported usin ... Y R

TPA-1228 GDI-78: The equipment/subsystem containers, covers (for op ...

Y R

TPA-1229 GDI-79: The equipment/subsystem transport container shall ...

Y R

TPA-1230 GDI-80: The equipment/subsystem storage container shall be ...

Y R

TPA-2846 GDI-3910: The dew point shall never be reached inside the co ...

Y R

TPA-2847 GDI-3911: The pressure inside the container shall be 10 to 1 ...

Y R


Y R


Y R


Y R

TPA-2851 GDI-3909: Simple equipment/subsystem container shall be equi ...

Y I


Y R

TPA-2853 GDI-3913: The IATA flight regulations shall be considered. ...

Y R


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TPA-2854 GDI-3914: For safety reasons, the equipment/subsystem transp ...

Y R

TPA-2855 GDI-3916: Flight altitude of 30 000 feet shall be considered ...

Y A

TPA-2856 GDI-3915: Maximum rates of air pressure change: 1,43 mbar/se ...

Y R

3.1.8.2 Equipment/Subsystem Packing TPA-1232 GDI-90:

Where applicable blanking caps shall be fitted to ... Y I

TPA-1233 GDI-91: All equipment shall be packaged to ensure that it ...

Y I

TPA-1234 GDI-93: The specified item GSE shall follow as far as appr ...

Y I

3.1.8.3 Container Identification TPA-1236 GDI-95:

Each container shall be labelled, tagged or marked ... Y I

TPA-1237 GDI-96: In addition to the above, the container shall also ...

Y I

TPA-1238 GDI-2267: Size of company labels on containers shall be agre ...

Y R

3.1.8.4 Handling TPA-1240 GDI-98:

Equipment/subsystem weighing more than 10 kg shall ... Y R

3.1.9 Seals TPA-1242 GDI-100:

Any seals used shall comply with all the applicabl ... Y R

TPA-1243 GDI-101: Any seals requiring periodic replacement during gr ...

Y R

3.1.10 Lubricants and Sealants TPA-1245 GDI-103:

No lubricants or sealants shall be used without th ... Y R

3.2 Mechanical Design and Interface Requirements TPA-1248 GDI-105:

All drawings, specifications and engineering data ... Y R

TPA-1249 GDI-106: Equipment/subsystem shall be compatible with mecha ...

Y R

TPA-1253 GDI-2137: Material selection shall be in accordance with ECS ...

Y R

TPA-1254 GDI-2138: For pyrotechnics ECSS-E-30 Part 6 shall apply. ...

Y R

TPA-1255 GDI-2139: Mechanical parts selection shall be in accordance ...

Y R

TPA-2857 GDI-3980: All reference frames shall be right-handed orthogo ...

Y R

3.2.2 Structural Design 3.2.2.1 General Requirements TPA-1258 GDI-117:

The following failure modes, for equipment/subsyst ... Y A

TPA-1259 GDI-118: For all structural items the following analyses ar ...

Y A

TPA-1260 GDI-119: Dynamic Analysis: The dynamic analysis shall show ...

Y A


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TPA-1261 GDI-120: Static Analysis: The analysis shall identify and r ...

Y A

TPA-1262 GDI-121: Stress Analysis: For each item a complete stress/s ...

Y A

TPA-1263 GDI-122: No yielding is allowed at proof load/proof pressur ...

Y T

TPA-1264 GDI-2053: The structure shall be of adequate strength to wit ...

Y A

TPA-1265 GDI-2054: Local buckling shall be tolerated only if it is re ...

Y A

TPA-1266 GDI-2055: For composite materials, microbuckling of fibers s ...

Y A

TPA-1267 GDI-123: The equipment/subsystem shall be designed to withs ...

Y A

TPA-1268 GDI-124: For sine and random vibrations, the mechanical siz ...

Y A

TPA-1269 GDI-125: Wherever practical in the design of the primary st ...

Y A

TPA-1270 GDI-126: Redundancy concepts (fail-safe) shall be considere ...

Y A

TPA-1271 GDI-127: Fracture control principles shall be applied where ...

Y A

TPA-1272 GDI-128: In cases where a fail-safe design cannot be implem ...

Y A

TPA-1273 GDI-134: Fasteners used in safe life applications, items fa ...

Y A

TPA-1274 GDI-135: Fasteners a. Fasteners shall be classified and ana ...

Y A

TPA-1275 GDI-137: Non-metallic flight structural items (composite, g ...

Y T

TPA-1276 GDI-138: For load cases involving thermal and/or moisture d ...

Y A

TPA-1277 GDI-139: Where pressure and/or temperature and/or moisture ...

Y A

TPA-1278 GDI-140: The Flight equipment shall be able to survive 4 ti ...

Y A

3.2.2.2 Mass Properies TPA-1280 GDI-143:

All equipment/subsystem suppliers shall provide eq ... Y R

TPA-1282 GDI-146: The mass of an item must be measured with the foll ...

Y T

3.2.2.3 Centre of Gravity and Moment of Inertia TPA-1284 GDI-148:

All COG and MOI estimates shall be accompanied by ... Y A

TPA-1285 GDI-149: The Center of Gravity (CoG) shall be given. w.r.t. ...

Y R

TPA-1286 GDI-150: The Moments of Inertia (MoI) shall be given about ...

Y R

3.2.2.4 Stiffness requirements TPA-1288 GDI-2140:

Minimum natural frequency requirements are imposed ... Y A


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TPA-1289 GDI-154: Except otherwise specified, when equipment/subsyst ...

Y T,A

TPA-1290 GDI-155: Modal analysis shall be performed to verify the fr ...

Y T,A

TPA-1293 GDI-2188: The units and associated transport containers shal ...

Y A

TPA-1294 GDI-2189: Vertical and horizontal loads shall be considered ...

Y A

TPA-1300 GDI-2199: The transportation containers shall be designed to ...

Y A

TPA-1301 GDI-2200: The MGSE design and analysis shall consider a desi ...

Y A

3.2.2.6 Strength requirements 3.2.2.6.1 Definitions and General Requirements 3.2.2.6.2 Margins of Safety and Factors of Safety TPA-1323 GDI-186:

An uncertainty factor Jf shall be defined to provi ... Y A

TPA-1324 GDI-187: A Qualification Factor of 1.5 shall be used for KQ ...

Y T

TPA-1325 GDI-188: An Acceptance Factor of 1.0 shall be used for KA t ...

Y A

TPA-1326 GDI-189: A Design Factor of 1.5 shall be used for DF to det ...

Y A

TPA-1328 GDI-194: The unit shall be able to withstand, without failu ...

Y A

TPA-1329 GDI-195: Margin of safety (MOS) a. Margins of safety (MOS) ...

Y A

TPA-1330 GDI-197: Minimum Factors of Safety against ultimate for pre ...

Y A

TPA-1331 GDI-198: For combined loads where L(P) is the load due to m ...

Y A

TPA-2858 GDI-3229: Table [SRD-3782]: Minimum Factors of Safety ...

Y A

TPA-1334 GDI-207: Conservative friction coefficients regarding minim ...

Y A

TPA-1335 GDI-208: Wherever applicable, for general design of bolts, ...

Y R

TPA-1336 GDI-209: In addition, in case of combined loads due to ther ...

Y A

TPA-2859 GDI-3398: The design loads for the structure elements are t ...

Y A

TPA-2860 GDI-3400: The internal loads (thermo elastic, pre-stressed ...

Y A

TPA-2861 GDI-3401: For sine and random vibrations, the mechanical siz ...

Y A

3.2.3 Design Requirements 3.2.3.1 Mounting Requirements TPA-1340 GDI-219:

The attachment points of the equipment/subsystem s ... Y R

TPA-2862 GDI-3995: The attachment points shall provide a controlled s ...

Y I,R


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TPA-2863 GDI-3996: The mechanical mounting interface shall be consist ...

Y R

TPA-1341 GDI-220: The number of attachement bolts for a equipment sh ...

Y A

TPA-1342 GDI-221: The interface plane flatness of a equipment/subsys ...

Y I

TPA-1343 GDI-222: The equipment/subsystem bolts type and number shal ...

Y R

TPA-1344 GDI-223: Except otherwise specified, all equipment/subsyste ...

Y R

TPA-1345 GDI-228: Unless special conditions override, the thickness ...

Y R

TPA-1346 GDI-229: Minimum clearance between mechanical parts shall c ...

Y R

TPA-1347 GDI-230: All equipment/subsystems shall be designed allowin ...

Y A

TPA-1348 GDI-2550: The minimum load carrying capability of the insert ...

Y A,R

TPA-1349 GDI-2551: The following typical insert distances along the m ...

Y A,R

3.2.3.2 Alignment Requirements TPA-1351 GDI-232:

Equipment/subsystems requiring alignment with an a ... Y R

TPA-1352 GDI-233: Optical references are required to withstand all t ...

Y R

TPA-1353 GDI-234: Location of optical references for equipment/subsy ...

Y R

TPA-1354 GDI-235: The alignment errors shall be included in pointing ...

Y R

TPA-1355 GDI-236: Equipment/subsystems which require alignment accur ...

Y R

TPA-2864 GDI-3405: No equipment/subsystem shall generate microvibrati ...

Y A,R

TPA-2865 GDI-3998: Equipment/subsystems sensitive to microvibration l ...

Y A,R

TPA-2866 GDI-3815: The compatibility of the allowable microvibration ...

Y A

3.2.4 Mechanical / Optical Interface Control Documents TPA-1357 GDI-239:

The mechanical and optical configuration and its i ... Y A

TPA-1358 GDI-240: Interfaces will be subjected to a formal inspectio ...

Y T,I

TPA-1359 GDI-241: The issues of ICDs have to be released as defined ...

Y A

TPA-1360 GDI-242: One of the attachment holes on a equipment/subsyst ...

Y R

TPA-1361 GDI-243: The equipment/subsystem reference frame shall have ...

Y R

TPA-1362 GDI-244: The equipment/subsystem alignment reference frame ...

Y R

TPA-1363 GDI-246: The dimensioning of the attachment hole pattern sh ...

Y A

TPA-1364 GDI-247: Interface Control Drawings shall be provided to AS ...

Y R


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3.2.5 Mechanical Mathematical Model Requirements TPA-1366 GDI-253:

Detailed Finite Element Models (FEM) shall be prov ... Y A

TPA-2867 GDI-3830: Detailed Finite Element Models (FEM) shall be prov ...

Y A

TPA-1367 GDI-254: All FE model requirements, checks and formats are ...

Y T

3.3 Mechanism Design 3.3.1.1 Engineering Requirements TPA-1369 GDI-2141:

The mechanism engineering shall consider every pha ... Y A

TPA-1370 GDI-821: Mechanisms shall be functionally analysed to deter ...

Y A

3.3.1.2 Mechanism Function TPA-1372 GDI-2142:

The mechanism shall provide structural support to ... Y R

TPA-1373 GDI-2143: The kinematic requirements applicable to each posi ...

Y R

TPA-1374 GDI-2144: The envelopes within which each moving part is all ...

Y R

3.3.1.3 Redundancy TPA-1377 GDI-827:

Redundancy a. During the design of the mechanism a ...

Y A

3.3.1.4 Storage and Maintenance TPA-1379 GDI-847:

All mechanisms shall be able to perform nominally ... Y R

TPA-1380 GDI-2152: The mechanisms shall not require any periodic main ...

Y R

TPA-1381 GDI-2145: Activations of mechanisms after a period of storag ...

Y R

3.3.1.5 Parts and Components TPA-1383 GDI-2158:

Existing (commercially available or off-the-shelf) ... Y R

3.3.1.6 Lubrication TPA-1385 GDI-2160:

a. Mechanisms shall be designed to provide adequat ... Y R

3.3.1.7 Design Life TPA-1387 GDI-844:

Mechanisms shall be designed for a lifetime coveri ... Y T,A

TPA-1388 GDI-2164: The cycle definition is subject to agreement with ...

Y R

TPA-1389 GDI-1096: Paragraph 4.8.2 (Verification by Analysis) of ECSS ...

Y A

TPA-1390 GDI-1097: Paragraph 4.8.3 (Verification by Test) of ECSS-E-3 ...

Y T

3.3.2 Mechanical Design and Sizing TPA-1392 GDI-2173:

Mechanisms shall be designed to meet the mechanica ... Y T,A,R

3.3.2.2 Structural Dimensioning TPA-1394 GDI-822:

The structural parts of the mechanism shall meet t ... Y T,A,R

TPA-1395 GDI-2174: Mechanisms shall conform to the specified stiffnes ...

Y A


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TPA-1396 GDI-2115: Loads shall be derived according to requirements s ...

Y R

TPA-1397 GDI-2702: a. The operational loads of the mechanisms shall b ...

Y R

3.3.2.3 Factors of Safety TPA-1399 GDI-2176:

Mechanisms shall be designed with a positive margi ... Y A

TPA-1400 GDI-2703: a. In the computation of safety margins the follow ...

Y A

TPA-1401 GDI-828: The following specific factors of safety shall app ...

Y A

3.3.2.4 Functional Dimensioning (Motorization) TPA-1403 GDI-2185:

a. Actuators (electrical, mechanical, thermal and ... Y T,A

TPA-1404 GDI-2186: The Sub-Contractor of recurring equipment/subsyste ...

Y R

TPA-1405 GDI-2184: Elements to be deployed in orbit (or otherwise sho ...

Y T

TPA-1406 GDI-2221: Unless monitored at spacecraft system level, the d ...

Y R

TPA-2869 GDI-1098: Full deployment status of one-shot drivable mechan ...

Y T

TPA-1407 GDI-1099: Mechanisms (except the "single shot" type) shall b ...

Y R

TPA-1408 GDI-1100: The status of mechanisms that are locked during la ...

Y T

TPA-1409 GDI-1101: The capability shall be provided to monitor the va ...

Y T

TPA-1410 GDI-2203: Electrical Actuators a. When the actuation torque/ ...

Y A

TPA-1411 GDI-2218: Replaceable Elements All parts or components which ...

Y R

TPA-1412 GDI-2224: Latching or Locking a. Latching mechanisms used to ...

Y T,R

TPA-1413 GDI-2225: End-Stops a. Mechanisms with restricted travel or ...

Y A,R

TPA-1414 GDI-2226: Separable Contact Surfaces a. Separable contact su ...

Y A,R

TPA-1415 GDI-2227: Ball Bearings a. Ball bearings “manufactured from ...

Y R

TPA-1416 GDI-2228: Gears The dimensioning and sizing of gears shall b ...

Y R

TPA-1417 GDI-2229: Mechanical Clearance a. When designing and locatin ...

Y T,R


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TPA-1418 GDI-2230: Threaded Parts or Locating Devices a. All threaded ...

Y R

TPA-1419 GDI-2231: Venting a. Unless the mechanism is hermetically se ...

Y R

TPA-1420 GDI-2232: Release and Locking Devices a. All pyrotechnic and ...

Y R

3.3.2.8 Shock Emission Requirements TPA-1422 GDI-2712:

Shocks generated by activation of release mechanis ... Y T

TPA-1423 GDI-2711: Allowable shocks induced during any deployment lat ...

Y T,A

3.3.3 Electrical and Electronic Requirements 3.3.3.1 Electrical Design TPA-1426 GDI-2237:

a. Mechanisms shall be designed to meet all the re ... Y R

3.3.3.2 Insulation TPA-1428 GDI-2240:

a. Electrical wires shall be insulated from the st ... Y T,R

3.3.3.3 Grounding TPA-1430 GDI-2242:

a. Each mechanism shall be electrically bonded to ... Y T,R

3.3.3.4 Electrical Connectors TPA-1432 GDI-2250:

a. With the exception of the bonding strap for gro ... Y R

3.3.3.5 Over Current Protection TPA-1434 GDI-2252:

a. Mechanisms containing electrical parts and circ ... Y R

3.3.3.6 Strain on Wires TPA-1436 GDI-2254:

Moving cable harness shall have reproducible resis ... Y R

3.3.3.7 Magnetic Cleanliness and ESD or EMC Protection TPA-1438 GDI-2256:

Mechanisms shall conform to the spacecraft system ... Y A,R

3.3.4 Thermal Requirements 3.3.4.1 Thermal Design Requirements TPA-1441 GDI-2259:

a. The thermal design of the mechanism shall ensur ... Y A,R

TPA-1442 GDI-2261: Motors shall withstand their stalling torque for a ...

Y T,A

TPA-1443 GDI-2262: Mechanisms shall be shielded from Sun. If shieldin ...

Y R

3.3.4.2 MLI Requirements TPA-1445 GDI-2264:

a. When using MLI, supported at discrete positions ... Y R

3.4 Thermal Design and Interface Requirements TPA-2870 GDI-3179:

Chapter 3 of ECSS-E-30 Part 1 shall apply with the ... Y A

3.4.2 Definition of Temperatures and Terms 3.4.2.1 Radiatively Controlled Equipment/Subsystem TPA-1451 GDI-298:

In the frame of BepiColombo, all equipment/subsyst ... Y R


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3.4.2.2 Conductively Controlled Equipment/Subsystem TPA-1453 GDI-300:

All equipment/subsystems with a power density on t ... Y R

TPA-2871 GDI-3880: The heater power density shall not exceed 5W per a ...

Y R

3.4.2.3 Isothermal Equipment/Subsystem TPA-1455 GDI-302:

As far as possible thermal gradients across the ba ... Y R

TPA-1456 GDI-303: For radiative equipment/subsystems the temperature ...

Y T,A

TPA-1457 GDI-304: For conductive equipment/subsystems the temperatur ...

Y T,A

TPA-1458 GDI-305: For non-isothermal equipment/subsystems a referenc ...

Y R

3.4.2.4 Temperature Reference Point (TRP) TPA-1460 GDI-307:

The temperature reference point (TRP) shall be sel ... Y R

3.4.2.5 System Interface Temperature Point (STP) TPA-2873 GDI-3876:

The system interface temperature point (STP) if de ... Y T,A

TPA-2874 GDI-3882: The equipment/unit supplier shall analyse the heat ...

Y A

3.4.3 Thermal Interface Requirements 3.4.3.1 Conductive Interface TPA-1463 GDI-316:

The mounting interface shall comply with the mecha ... Y A

TPA-1464 GDI-317: Equipment/subsystem mounting areas shall not be pa ...

Y R

TPA-1465 GDI-318: All equipment/subsystems shall have a smooth and p ...

Y R

TPA-1466 GDI-319: Local heat flux shall not be greater than 1.5x spe ...

Y A

TPA-1467 GDI-2536: An interface filler with a coefficient of friction ...

Y R

3.4.3.2 Radiative Interface TPA-1469 GDI-322:

Equipment/subsystems shall be designed with an emi ... Y R

3.4.3.3 Internal Temperature Monitoring TPA-1471 GDI-324:

Temperature monitoring of selected points within a ... Y R

TPA-1472 GDI-325: The location, type and electrical interface of all ...

Y R

3.4.4 Thermal Design Requirements TPA-2875 GDI-3184:

Dimensioning of the Thermal Control of space expos ... Y A

TPA-2876 GDI-3881: Dimensioning of the standard Equipment/UnitThermal ...

Y A

TPA-1474 GDI-327: The equipment/subsystems shall be designed such th ...

Y A

TPA-2877 GDI-3185: All space exposed items shall be able to withstand ...

Y T,A

TPA-2878 GDI-3188: Use of materials with non-stable thermo-optical pr ...

Y T,R


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TPA-2879 GDI-3193: It shall be possible to demonstrate conformance of ...

Y T,A

TPA-2880 GDI-3203: Calculated temperatures of external materials shal ...

Y A

TPA-2881 GDI-3967: Every equipment/unit/subsystem which is exposed to ...

Y A

3.4.4.1 Design Requirements for MLI TPA-2883 GDI-3189:

Thermal insulation properties of actual configurat ... Y T

TPA-2884 GDI-3190: MLI blankets used on a Structural, Thermal and/or ...

Y R

TPA-2885 GDI-3191: The MLI used on the Flight Model of the spacecraft ...

Y R

TPA-2886 GDI-3192: It shall be possible to install/remove a complete ...

Y R

3.4.5 Thermal Control TPA-1476 GDI-331:

All thermal hardware mounted on the equipment/subs ... Y R

3.4.6 Thermal Interface Control Documents TPA-1478 GDI-333:

All equipment/subsystem thermal interfaces shall b ... Y R

3.4.7 Thermal Mathematical Model Requirements 3.4.7.1 Thermal Analyses TPA-2888 GDI-3201:

The compliance to the thermal performance requirem ... Y A

TPA-2889 GDI-3202: In case of TB test execution, the temperature unce ...

Y A

3.4.7.2 Thermal Interface Modeling TPA-1481 GDI-336:

The Thermal mathematical model shall be provided f ... Y A

TPA-1482 GDI-337: SI units: All units used in thermal models (geomet ...

Y A

3.4.7.3 Thermal Model Correlation TPA-1484 GDI-339:

The detailed thermal model of a equipment/subsyste ... Y T,A

3.4.7.4 Reduced Thermal Model TPA-1486 GDI-341:

The consistency between reduced and detailed therm ... Y A

TPA-1487 GDI-342: The convergence of the thermal models shall be dem ...

Y A

3.6.1 General Requirements TPA-1489 GDI-380:

All electrical performances are specified under Wo ... Y R

TPA-1490 GDI-381: Beginning-Of-Life criteria shall be derived by the ...

Y R

3.6.2 Electrical Power 3.6.2.1 Power Requirements and Budgets TPA-1494 GDI-1824:

For all units with a primary power consumption whi ... Y R

TPA-1495 GDI-1825: The power for telemetry conditioning of equipment ...

Y R

3.6.2.2 Failure Containment and Redundancy


of 77




TPA-1499 GDI-1826: Any protection feature supporting essential functi ...

Y R

TPA-1500 GDI-1827: With the exception of protection features such as ...

Y A

TPA-1501 GDI-1828: Recovery of primary power shall be possible in any ...

Y A

3.6.2.3 Power Conditioning and Control TPA-1503 GDI-1830:

The phase margin of converters and regulators shal ... Y T,A

TPA-1505 GDI-1832: The electrical zero-volt reference of isolated con ...

Y T

TPA-1506 GDI-1833: The capacitance between the zero-volt reference of ...

Y T

TPA-1507 GDI-1834: If a switching converter is externally synchronise ...

Y R

TPA-1508 GDI-1835: Under the occurrence of any single failure, the co ...

Y A

3.6.2.3.2 Electrical Power User Interaction TPA-2891 GDI-3991:

The requirements on electrical power user interact ... Y R

TPA-2892 GDI-3992: All load requirements shall be verified by test. ...

Y T

TPA-2893 GDI-3205: No load shall generate a spurious response that ca ...

Y T

3.6.2.4 Power Distribution and Protection TPA-1510 GDI-393:

Fuses shall not be used. ... Y R

3.6.2.4.1 28V Regulated Power Requirements TPA-1512 GDI-410:

All equipment/subsystems connected to the regulate ... Y T,A

TPA-1513 GDI-411: If undervoltage protection is implemented by the l ...

Y T

TPA-1514 GDI-412: In case of an inductive load, the load shall preve ...

Y T,A

TPA-1515 GDI-413: The load shall not be irreversibly degraded for an ...

Y R

TPA-1516 GDI-415: No primary current protection shall be implemented ...

Y R

TPA-1517 GDI-417: All electronic logic equipment/subsystems/circuits ...

Y I,R

TPA-1518 GDI-418: All power converters shall work in free-running mo ...

Y T

TPA-1519 GDI-419: The free-running frequency shall be limited to ±10 ...

Y T

TPA-1520 GDI-420: The as designed free-running frequency and frequen ...

Y T

TPA-1521 GDI-421: The equipment/subsystems shall be designed taking ...

Y A

TPA-1522 GDI-416: 28V Regulated Latching Current Limiter Interface C ...

Y T

TPA-1523 GDI-424: 28V Regulated Fold-Back Current Limiter Interface ...

Y T

TPA-1524 GDI-426: Following switch-ON, and during input filter charg ...

Y T,R


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3.6.2.4.3 Power Consumption Requirements TPA-1526 GDI-433:

The compliance versus the power allocations shall ... Y T,A

TPA-1527 GDI-434: For each power interface circuit, the following co ...

Y T,A

TPA-1528 GDI-435: A power consumption test shall be required at temp ...

Y T,R

3.6.2.4.4 Tolerance to Power Bus Failures TPA-1530 GDI-437:

When a equipment/subsystem is internally redundant ... Y T,A

3.6.2.4.5 Initial Electrical Status TPA-1532 GDI-439:

After being switched ON, equipment shall have a sa ... Y T

3.6.6 Discrete Standard Signal Interfaces 3.6.6.1 General Definitions and Conventions TPA-1634 GDI-450:

Specified driver (or source) characteristics shall ... Y R

TPA-1635 GDI-451: All data and signal interface drivers shall surviv ...

Y T,A

TPA-1636 GDI-452: The equipment/subsystem shall tolerate active sign ...

Y T,A

TPA-1637 GDI-453: In case the electrical architecture does foresee c ...

Y T,R

TPA-1638 GDI-454: In case no load is specified, the interface charac ...

Y R

3.6.6.2 Interface Control during Power Cycling TPA-1640 GDI-2278:

Input interfaces shall not be damaged or harmed du ... Y A

TPA-1641 GDI-2279: Output interfaces shall not be damaged or harmed d ...

Y A

TPA-1642 GDI-2280: For pulse commands it shall be ensured that spurio ...

Y A

TPA-2894 GDI-478: The SBDL interface is dedicated to serial digital ...

Y R

TPA-2895 GDI-486: Standard Balanced Digital Link interface: The (sub ...

Y T

TPA-2896 GDI-2496: The following conditions shall apply for use of th ...

Y R

TPA-2897 GDI-2497: The SBDL receiver implementation shall allow to po ...

Y R

3.6.6.4.1 Analogue Telemetry Acquisition (AN1) TPA-1644 GDI-511:

Analogue telemetry Acquisition -5V to +5V interfac ... Y T

3.6.6.5 Temperature Acquisitions 3.6.6.5.1 Thermistor Type 1: YSI-44907/YSI-44908 (ANY) TPA-1647 GDI-523:

Temperature Acquisition Type 1: YSI-44907/YSI-4490 ... Y T

3.6.6.5.2 Thermistor Type 2: PT-1000 (ANP) TPA-1649 GDI-526:

Temperature Acquisition Type 2: PT-1000 (ANP) inte ... Y T

3.6.6.6.2 Relay / Switch Status Interface TPA-2899 GDI-488:

The open/closed status of a relay/switch contact o ... Y T


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TPA-2900 GDI-489: The Relay / Switch Status interface receivers shal ...

Y A,R

TPA-2901 GDI-546: Relay / Switch Status Acquisition Interface The (s ...

Y T

3.6.8 Connectors and Harness General Design Requirements

TPA-1653 GDI-574: The spacecraft harness categorisation into EMC cla ...

Y R

TPA-1654 GDI-2576: Equipment/subsystems shall use a separate connecto ...

Y R

TPA-1655 GDI-2577: Signals falling into different EMC categories shal ...

Y R

TPA-1656 GDI-583: Nominal and redundant lines/functions shall be rou ...

Y R

TPA-1685 GDI-592: All unterminated equipment or harness connectors s ...

Y I,R

TPA-1686 GDI-593: All arming plugs shall be protected by EMC backshe ...

Y R

3.6.8.1 Connector Types TPA-1658 GDI-572:

All connectors mounted on equipment/subsystems and ... Y R

TPA-1659 GDI-2575: Where non-standard connector, inserts, or round co ...

Y R

TPA-1660 GDI-582: Connectors shall be made of Non-magnetic material ...

Y R

TPA-1661 GDI-573: The number times flight connectors are mated / dem ...

Y R

3.6.8.2 Connector Characteristics TPA-1663 GDI-576:

Connectors at interfaces shall be clearly identifi ... Y R

TPA-1664 GDI-577: Equipment or structure-mounted connectors/contacts ...

Y R

TPA-1665 GDI-578: As far as possible, the connector type used for pr ...

Y R

TPA-1666 GDI-2588: The EED mating (harness) connector shall be of MS ...

Y R

TPA-1667 GDI-2585: If power and other signal connectors are located a ...

Y R

TPA-1668 GDI-587: Mechanical methods in conjunction with identificat ...

Y R

TPA-1669 GDI-610: All connectors shall be marked unambiguously. Labe ...

Y R

TPA-1670 GDI-2578: Equipment or structure-mounted connectors shall be ...

Y R

TPA-1671 GDI-581: Each signal and its corresponding return shall, wh ...

Y R

TPA-1672 GDI-2579: An adequate number of spare contacts shall be made ...

Y R

TPA-1673 GDI-2580: If a connector contains only shielded wires only 8 ...

Y R

TPA-1674 GDI-2581: Connectors shall be fully equipped with contacts ( ...

Y I


of 77




TPA-1675 GDI-589: At least one contact per equipment connector shall ...

Y R

TPA-1676 GDI-2583: In case several shield connections through a conne ...

Y R

3.6.8.3 Connector Mounting TPA-1678 GDI-585:

All electrical connectors shall be located at a mi ... Y R

TPA-1679 GDI-586: Connectors shall be arranged in such a way that th ...

Y R

TPA-1680 GDI-2582: D*M(A)-type connectors mounting clearances shall b ...

Y I,R

TPA-1681 GDI-580: Male and female connectors shall be mechanically l ...

Y I

TPA-2902 GDI-3950: For D*M(A)-type connectors the wall thickness shal ...

Y R

TPA-2903 GDI-3951: For D*M(A)-type connectors the female screw lock a ...

Y R

TPA-1682 GDI-588: Connector savers shall be utilized on all flight s ...

Y I

3.6.8.4 Test Connectors TPA-1684 GDI-591:

Test connectors shall have sufficient protection t ... Y R

3.6.8.5 Cabling / Wiring TPA-2904 GDI-3124:

No piece of harness shall be used as a mechanical ... Y R

TPA-2905 GDI-3125: For transmission of power, each line shall be twis ...

Y R

TPA-2906 GDI-3211: The power distribution shall be protected in such ...

Y A

TPA-2907 GDI-3127: The harness inductance for a fully regulated bus, ...

Y A

TPA-1688 GDI-2587: For the power harness redundant contacts and wirin ...

Y R

TPA-1689 GDI-595: Cables falling into different EMC categorisations ...

Y R

TPA-1690 GDI-596: All cable bundles shall be routed as close as poss ...

Y I,R

TPA-1692 GDI-598: The DC resistance between the single cable shield ...

Y T

TPA-1693 GDI-2589: Electrical supply for each EED shall be by a separ ...

Y R

TPA-1694 GDI-2590: Connections to the pyro initiators shall be capabl ...

Y R

TPA-1695 GDI-2591: The safe plug shall short-circuit and ground each ...

Y R

TPA-1696 GDI-2592: The arming plug shall provide electrical continuit ...

Y R

3.6.8.6 Cable and Harness Shields TPA-1703 GDI-611:

To achieve a complete Faraday-cage around the harn ... Y R

TPA-1698 GDI-600: Where shielded wires are used, the shield shall be ...

Y R

TPA-1699 GDI-601: The structure termination of shields shall be made ...

Y I,R


of 77




TPA-1700 GDI-602: The maximum unshielded length of any shielded wire ...

Y R

TPA-1701 GDI-603: Daisy chaining of shield terminations shall be avo ...

Y R

TPA-1702 GDI-604: Shields shall not be used as an intentional curren ...

Y R

TPA-1704 GDI-612: Overall shields shall be terminated to the connect ...

Y R

3.6.8.7 Harness Capacitance TPA-1706 GDI-607:

Interface signal drivers shall consider the capaci ... Y A

3.6.9 Electrical Interface Control Document TPA-1708 GDI-621:

Interfaces will be formally controlled within the ... Y R

TPA-1709 GDI-2574: Electrical interface control data shall be transfe ...

Y R

3.7.1 Bit / Byte Numbering Convention TPA-2909 GDI-624:

In all project specific documentation including co ... Y T,R

TPA-2910 GDI-626: For serial data transfer, within any data type str ...

Y T,R

TPA-2911 GDI-746: The following standardization (Table GDI-747) shal ...

Y R

5.1 Mechanical Interface Datasheet TPA-1753 GDI-2760:

The mechanical and optical configuration and its i ... Y R

6.1 Thermal Interface Control Document TPA-2912 GDI-2892:

All unit thermal interfaces shall be described wit ... Y R

7.1 Electrical Interface Datasheets (Format) TPA-2913 GDI-2964:

The equipment/subsystem Electrical ICD shall provi ... Y R


of 77



8 E&T APPLICABILITY MATRIX







TPA-3052 ET-14273: The MCS coordinate system is shown below. The +Y a ...

Y R

TPA-3053 ET-36: Sine and random vibrations: The following mechanic ...

Y A,R

TPA-3054 ET-15090: Sinus Environment during Road Trans ...

Y A,R

TPA-3055 ET-15091: Random Virbation Environment during ...

Y A,R

TPA-3056 ET-15092: Standard Sinus environment during A ...

Y A,R

TPA-3057 ET-15094: Antonov 124 specific quasi-static l ...

Y A,R

TPA-3058 ET-15095: Antonov 124 specific crash load las ...

Y A,R

TPA-3059 ET-15096: Antonov 124 specific sinus vibratio ...

Y A,R

TPA-3060 ET-15098: The LV generated quasi-staic loads at satellite Co ...

Y A

TPA-3061 ET-15100: The LV generated sine vibration loads at the LV-Ad ...

Y A

TPA-3062 ET-15102: The LV generated random vibration loads at the LV- ...

Y A

TPA-3063 ET-210: System level sine vibration inputs] ...

Y T,A

TPA-3064 ET-212: Acoustic test spectra] ...

Y T,A

TPA-3065 ET-215: Shock environment of separation eve ...

Y T

TPA-3066 ET-15106: The following accelerations shall be considered du ...

Y A

TPA-3067 ET-14642: For external items the heatexchange and absorbed f ...

Y A

TPA-3068 ET-160: A generic unit/equipment/subsystem temperature lev ...

Y T,A,R


of 77




TPA-3069 ET-14757: For MTM units, the following temperature limits ap ...

Y T,A

TPA-3070 ET-14827: Structure Temperature limits (design temperatures) ...

Y A

TPA-3071 ET-14785: Propulsion Temperature limits (design temperatures ...

Y T,A

TPA-3072 ET-14892: Interface temperature limits for antennas and mech ...

Y T,A

TPA-3073 ET-249: All equipment shall be designed to withstand a rel ...

Y R

TPA-3074 ET-252: For AIV and storage, all equipment shall withstand ...

Y R

TPA-3075 ET-253: During transport prior to integration on the space ...

Y R

TPA-3076 ET-254: The flight hardware transportation containers shal ...

Y R

TPA-3077 ET-14284: For thermal analyses of orbiting spacecraft, in or ...

Y A,R

TPA-3078 ET-14288: The solar electromagnetic radiation includes infra ...

Y R

TPA-3079 ET-14287: In most of thermal applications, the solar spectru ...

Y R

TPA-3080 ET-14632: After encapsulation under the fairing, the spacecr ...

Y

TPA-3081 ET-14635: The typical mission timeline for BC is shown in ta ...

Y A

TPA-3082 ET-427: The nominal Solar constant in earth orbit is 1370 ...

Y A

TPA-3083 ET-429: The albedo factor is the ratio between the solar p ...

Y A

TPA-3084 ET-430: For short averaging time (t < 0.3 hr), the followi ...

Y A

TPA-3085 ET-431: The Earth and its atmosphere emit an infra-red rad ...

Y A

TPA-3086 ET-251: Units mounted on the S/C shall be designed to with ...

Y A,R

TPA-3087 ET-14628: The thermal flux density radiated by the fairing o ...

Y A

TPA-3088 ET-14626: The aerothermal flux after fairing jettison of 113 ...

Y A

TPA-3089 ET-14634: The spacecraft attitude during LEOP shall be consi ...

Y A

TPA-3090 ET-432: The thermal design shall allow lunar and earth ecl ...

Y A

TPA-3091 ET-428: The maximum spacecraft to sun distance shall be 1. ...

Y A

TPA-3092 ET-461: Solar and Planetary Electromagnetic Radiation ...

Y R

TPA-3093 ET-462: Neutral Atmosphere ...

Y R

TPA-3094 ET-463: Plasmas ...

Y R

TPA-3095 ET-464: Energetic Particle Radiation ...

Y R


of 77




TPA-3096 ET-465: Particulates ...

Y R

TPA-3097 ET-466: Contamination ...

Y R

TPA-3098 ET-467: Thermal (described in section 5) ...

Y R

TPA-3099 ET-15264: For many of the associated analyses it is necessar ...

Y A

TPA-3100 ET-14252: Average and worst case irradiance levels for the h ...

Y A

TPA-3101 ET-15112: The Table below gives the parameters which shall b ...

Y R

TPA-3102 ET-15299: For trapped radiation source term evaluation withi ...

Y A

TPA-3103 ET-15303: For solar particle events (solar protons) the refe ...

Y A

TPA-3104 ET-15302: To predict the fluences seen by BepiColombo an inv ...

Y A

TPA-3105 ET-15304: For analysing single event upset rates during sola ...

Y A

TPA-3106 ET-15306: CREME96 shall be the standard model for cosmic ray ...

Y A

TPA-3107 ET-15308: It is possible to make upset rate predictions only ...

Y A

TPA-3108 ET-15309: The CREME96 method shall be used [13], [14] for th ...

Y A

TPA-3109 ET-15310: The test data shall show the normalised upset rate ...

Y A

TPA-3110 ET-15312: The EQFRUX-Si or EQFRUX-Ga models shall be used fo ...

Y A

TPA-3111 ET-15314: Secondary radiation has to be analysed on a case-b ...

Y A

TPA-3112 ET-15316: The ionizing dose environment is represented by th ...

Y A

TPA-3113 ET-15317: The SHIELDOSE-2 model shall be used [16*] for ioni ...

Y A

TPA-3114 ET-15319: Damage to CCDs and other electro-optical component ...

Y A

TPA-3115 ET-15323: The solar proton spectrum which shall be applied f ...

Y A

TPA-3116 ET-15327: The galactic cosmic ray (GCR) LET spectrum which ...

Y A

TPA-3117 ET-15330: The BC spacecraft MCS elements shall be able to sa ...

Y A

TPA-3118 ET-15331: Peak fluxes (worst week, worst day, peak 5 minutes ...

Y A

TPA-3119 ET-15334: The source term of electrons at 0.39 AU shown in F ...

Y A

TPA-3120 ET-15339: The BC MCS elements shall withstand the effects of ...

Y A

TPA-3121 ET-15350: Devices (e. g. opto-electronics, glasses) which ar ...

Y A

TPA-3122 ET-15356: Table ET-15358 lists the types of testing which sh ...

Y T,R


of 77




TPA-3123 ET-14302: Contamination and cleanliness requirements are add ...

Y R

TPA-3124 ET-15038: ECSS-E-10-03A shall apply with the modifications d ...

Y

TPA-3125 ET-105: Qualification of the design shall be accomplished ...

Y R

TPA-3126 ET-14256: The objective of the qualification shall be to dem ...

Y T,A

TPA-3127 ET-14258: The test specimen shall be subjected to qualificat ...

Y T

TPA-3128 ET-14259: The test conditions shall not exceed design margin ...

Y T,R

TPA-3129 ET-14260: Items which can be qualified by an applicable qual ...

Y T,R

TPA-3130 ET-14261: Qualification testing shall be conducted at the re ...

Y R

TPA-3131 ET-107: Environmental acceptance testing shall be performe ...

Y T

TPA-3132 ET-14263: During environmental acceptance testing, condition ...

Y T

TPA-3133 ET-109: The objective of the test item functional performa ...

Y T,A

TPA-3134 ET-14265: An initial and a final functional performance test ...

Y T

TPA-3135 ET-14266: Intermediate functional performance tests, which m ...

Y T

TPA-3136 ET-14267: A functional performance test may run continuously ...

Y T

TPA-3137 ET-14268: The test shall be conducted under standard laborat ...

Y R

TPA-3138 ET-14269: The tests shall be performed in compliance with ap ...

Y T

TPA-3139 ET-14270: Failure detection, isolation and recovery function ...

Y T

TPA-3140 ET-14271: Functional test will be performed by operating all ...

Y T

TPA-3141 ET-111: Any test facility to be used within the instrument ...

Y A,R

TPA-3142 ET-113: The accuracy of instrument and test equipment used ...

Y A,R

TPA-3143 ET-115: The allowed test condition tolerances shall be app ...

Y A,I,R

TPA-3144 ET-119: Unless otherwise specified herein, all measurement ...

Y A,I,R

TPA-3145 ET-14276: The cleanliness requirements for the test items du ...

Y A,I,R

TPA-3146 ET-121: Test execution shall be started only if all starti ...

Y A,I,R

TPA-3147 ET-14277: Prior to and after every environmental test activi ...

Y I

TPA-3148 ET-14279: Before commencing any formal qualification or acce ...

Y R

TPA-3149 ET-14278: After completion of all formal qualifications or a ...

Y R


of 77




TPA-3150 ET-123: The test is successfully performed if all measurem ...

Y T,A

TPA-3151 ET-14280: Modifications, repair, replacement or refurbishmen ...

Y T,A

TPA-3152 ET-127: The unit/equipment/subsystem under test shall be m ...

Y T

TPA-3153 ET-128: At least one triaxial sensor shall be mounted on t ...

Y T

TPA-3154 ET-129: At least two axis aligned sensors shall be mounted ...

Y T

TPA-3155 ET-130: All unit/equipment/subsystems powered on during la ...

Y T

TPA-3156 ET-15033: Any need for notching shall be notified to ASD as ...

Y T,A

TPA-3157 ET-133: The test item shall be attached to the vibration e ...

Y T

TPA-3158 ET-134: The variation of transmissibility between test ite ...

Y T

TPA-3159 ET-135: Adequate fixture design and specimen installation ...

Y T

TPA-3160 ET-136: A pre-test of the empty fixture shall be performed ...

Y T

TPA-3161 ET-202: In case of large and heavy test items (e.g. module ...

Y

TPA-3162 ET-203: Proof testing of test adapters is specified in the ...

Y T

TPA-3163 ET-138: Frequency search tests shall be conducted in order ...

Y T

TPA-3164 ET-140: Frequency search tests shall be conducted along ea ...

Y T

TPA-3165 ET-14312: Units mounted on the spacecraft shall be designed ...

Y T,A

TPA-3166 ET-14391: Units mounted on the spacecraft shall be designed ...

Y T,A

TPA-3167 ET-14434: After freeze of unit accommodation the loads as de ...

Y R

TPA-3168 ET-14590: Units shall be designed and tested to withstand wi ...

Y T,A,R

TPA-3169 ET-149: Sine and random vibration tests shall be performed ...

Y T

TPA-3170 ET-150: Prior and after sine and random vibration qualific ...

Y T

TPA-3171 ET-151: Before applying full levels, a test at intermediat ...

Y T

TPA-3172 ET-152: Any notching must be formally requested as a waive ...

Y T

TPA-3173 ET-153: The vibration facility shall include a shock free ...

Y T

TPA-3174 ET-155: Unit/equipment/subsystems shall demonstrate by tes ...

Y T

TPA-3175 ET-156: Prior and after shock tests a low level sine frequ ...

Y T

TPA-3176 ET-14624: Shock testing shall be performed with a device pr ...

Y T


of 77




TPA-3177 ET-14625: The qualification to shock has to be demonstrated ...

Y T

TPA-3178 ET-158: Static tests shall be performed by applying static ...

Y T

TPA-3179 ET-231: The following temperature margins shall be taken f ...

Y T

TPA-3180 ET-162: The temperatures shall be selected and controlled ...

Y R

TPA-3181 ET-163: The test arrangement shall be as shown in Figure E ...

Y R

TPA-3182 ET-164: The unit/equipment/subsystem shall be bolted to a ...

Y R

TPA-3183 ET-165: On all external surfaces flight representative the ...

Y R

TPA-3184 ET-166: The heat sink (HS) plates shall be black painted ( ...

Y R

TPA-3185 ET-167: The conductive heat sink temperature and the chamb ...

Y R

TPA-3186 ET-168: For vacuum tests the pressure inside the chamber s ...

Y R

TPA-3187 ET-172: unit/equipment/subsystem’s suppliers shall perform ...

Y T

TPA-3188 ET-174: The TV test on unit/equipment/subsystem level shal ...

Y R

TPA-3189 ET-176: The unit/equipment/subsystems shall be tested foll ...

Y T,R

TPA-3190 ET-182: unit/equipment/subsystem suppliers shall perform t ...

Y T

TPA-3191 ET-183: The thermal vacuum acceptance test shall be perfor ...

Y T,R

TPA-3192 ET-187: unit/equipment/subsystem suppliers shall perform t ...

Y T

TPA-3193 ET-188: The thermal vacuum protoflight test shall be perfo ...

Y T,R

TPA-3194 ET-191: With regard to radiation testing the manufacturer ...

Y R

TPA-3195 ET-193: With regard to unit/equipment/subsystem EMC testin ...

Y R

TPA-3196 ET-15042: With regard to unit/equipment/subsystem ESD testin ...

Y R

TPA-3197 ET-195: A life test shall be required for all the assembli ...

Y T,R

TPA-3198 ET-197: Space conditioning shall be performed whenever des ...

Y T,R

TPA-3199 ET-198: The contractors shall propose the corresponding te ...

Y R

TPA-3200 ET-199: For example, but without limitation to, materials ...

Y T

11.1 SCOPE 11.2 Mechanical Test Objectives 11.3 Notching Pilosophy 11.4 Essential Rules 11.5 Notching Sine Test Spectrum 11.6 Notching Random Test Spectrum


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11.6.1 General Notching Criteria 11.6.2 Detailed Notching Criteria 11.6.2.1 Notching of a single resonance 11.6.2.2 Notching of a multi DOF equipment 11.6.2.3 Combined interface loads 11.6.3 Notching during tests 11.6.3.1 Identification of eigen modes 11.6.3.2 Determination of the interface loads 11.6.3.3 Determination of the notched spectrum 11.6.3.4 Random Tests at intermediate levels 11.6.3.5 Measurement plan 11.7 Random notching example


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9 EMC APPLICABILITY MATRIX







TPA-3221 EMC-545: Class "R" Bonds shall be made by direct metal to m ...

Y R

TPA-3222 EMC-529: The contact surface area of the two items to be bo ...

Y R

TPA-3223 EMC-530: Class R bonds shall be assembled so that a DC resi ...

Y T

TPA-3224 EMC-735: Class "R" bonds shall be verified in both directio ...

Y T

TPA-3225 EMC-531: Where bond straps are required for class R bond pu ...

Y A

TPA-3226 EMC-532: The bond shall have an adequate cross section to c ...

Y A

TPA-3227 EMC-536: Bonding of metallic surfaces shall be made by meta ...

Y R

TPA-3228 EMC-537: The assembled class S bond (i.e. metallic strap / ...

Y T

TPA-3229 EMC-553: Bonding for powered equipment not requiring a zero ...

Y T

TPA-3230 EMC-554: The bond assembly shall be sized to carry 150% of ...

Y A

TPA-3231 EMC-388: Joint faces shall be flat and clean before assembl ...

Y I,R

TPA-3232 EMC-559: To prevent corrosion and alloying, bonding of elec ...

Y A

TPA-3233 EMC-560: Where dissimilar materials are to be bonded, the r ...

Y A

TPA-3234 EMC-669: A suitable anti-corrosion coating shall be applied ...

Y R

TPA-3235 EMC-859: Conformance to electrical bonding requirements sha ...

Y R

TPA-3236 EMC-398: Structural elements including connector brackets, ...

Y T,R

TPA-3237 EMC-645: All housing parts, including connector recepticles ...

Y T

TPA-3238 EMC-644: Across Movable parts, a bond strap shall be applie ...

Y T

TPA-3239 EMC-590: Across movable conductive structural parts which f ...

Y T,R

TPA-3240 EMC-400: For CFRP structure without shielding function, the ...

Y T,R

TPA-3241 EMC-655: For CFRP structure used for electromagnetic shield ...

Y T

TPA-3242 EMC-656: Aluminium honeycomb shall be bonded to the Ground ...

Y T


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TPA-3243 EMC-658: The DC resistance between any other conductive com ...

Y T

TPA-3244 EMC-406: Mechanical Parts without electrical nor shielding ...

Y T,R

TPA-3245 EMC-592: Conductive structural elements which form part of ...

Y T,R

TPA-3246 EMC-407: Mechanical Parts used for electromagnetic shieldin ...

Y T,R

TPA-3247 EMC-693: The cable harness overall shield is considered to ...

Y R

TPA-3248 EMC-694: A long the harness length the average distance bet ...

Y T,R

TPA-3249 EMC-695: All metalic and metalised layers of Multi Layer In ...

Y T,R

TPA-3250 EMC-677: The BepiColumbo Grounding Concept shall be governe ...

Y A,R

TPA-3251 EMC-683: The concept shall be implemented through the use o ...

Y R

TPA-3252 EMC-687: The location of this point shall be chosen so as t ...

Y A,R

TPA-3253 EMC-688: Interconnection of the dedicated ground reference ...

Y R

TPA-3254 EMC-705: The distributed prime power shall not be utilised ...

Y R

TPA-3255 EMC-703: The Ground Reference for the generated secondary V ...

Y T

TPA-3256 EMC-437: Grounding: All secondary power supplies, inside a ...

Y I,R

TPA-3257 EMC-439: Power distributed between units (1 supplier; 1 rec ...

Y R

TPA-3258 EMC-440: Power distributed between units (1 supplier; sever ...

Y R

TPA-3259 EMC-719: Specific care shall be taken to avoid grounding lo ...

Y R

TPA-3260 EMC-441: After grounding, the impedance between the unit se ...

Y T

TPA-3261 EMC-438: Isolation: Prior to connection of the unit interna ...

Y T,R

TPA-3262 EMC-445: Grounding of signal circuits interfacing between S ...

Y R

TPA-3263 EMC-446: Where single-ended signal transmitters are used, i ...

Y R

TPA-3264 EMC-447: The use of common signal return paths is to be dis ...

Y R

TPA-3265 EMC-721: With the exception of declared Rf signals the use ...

Y R

TPA-3266 EMC-726: Interface circuits (with the exception of selected ...

Y T

TPA-3267 EMC-410: Each unit shall provide a grounding point, which i ...

Y I

TPA-3268 EMC-415: All units shall have a M4 bonding stud ...

Y I

TPA-3269 EMC-417: The resistance between the bonding stud and the un ...

Y T


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TPA-3270 EMC-442: A grounding diagram showing the implementation of ...

Y I

TPA-3271 EMC-727: The minimum content of each grounding diagram shal ...

Y I

TPA-3272 EMC-1328: The symbols shown in figure EMC-1347 below shall b ...

Y R

TPA-3273 EMC-449: EGSE signal and power circuits interfacing with fl ...

Y R

TPA-3274 EMC-411: CFRP and SiC shall not be used as an electrical bo ...

Y R

TPA-3275 EMC-419: Space exposed Insulating material having a surface ...

Y R

TPA-3276 EMC-425: PAINTS: Refer to PA Section above. ...

Y R

TPA-3277 EMC-426: HEATERS & THERMISTORS: Heaters, thermistors and o ...

Y T,R

TPA-3278 EMC-413: The structure of electrical and electronic units s ...

Y T

TPA-3279 EMC-697: Distances between screws for lids, etc... shall ne ...

Y R

TPA-3280 EMC-414: Discontinuities e.g. openings for ventilation, dra ...

Y A,I

TPA-3281 EMC-708: All harness and associated backshells shall form a ...

Y T,I

TPA-3282 EMC-891: Thermal hardware e.g. thermocouples and heatermats ...

Y R

TPA-3283 EMC-714: The electrical wiring harness shall be separated i ...

Y R

TPA-3284 EMC-715: The cables of each harness type shall be routed as ...

Y R

TPA-3285 EMC-885: Cable bundles shall be separated by at least 5cm w ...

Y R

TPA-3286 EMC-888: Test harness and connection access shall be config ...

Y R

TPA-3287 EMC-889: Thermal harness used during flight shall be catego ...

Y R

TPA-3288 EMC-716: Cable and shield shall be considered for each sign ...

Y R

TPA-3289 EMC-883: Each harness bundle shall have an overall shield o ...

Y I,R

TPA-3290 EMC-884: All cable shields shall be grounded at both ends, ...

Y T

TPA-3291 EMC-717: Use in preference order: MIL Round with approv ...

Y R

TPA-3292 EMC-1330: Shield termination at connectors shall be as shown ...

Y R

TPA-3293 EMC-803: Electromagnetic interference safety margins are ma ...

Y A

TPA-3294 EMC-804: A minimum acceptable safety margin is to be achiev ...

Y T,A

TPA-3295 EMC-818: A controlled grounding and isolation concept has b ...

Y R


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TPA-3296 EMC-801: The EMC Programme is controlled and documented by ...

Y R

TPA-3297 EMC-842: The submitted EMC Contol Plan shall co-ordinate th ...

Y R

TPA-3298 EMC-844: Verification matricies shall be established in acc ...

Y R

TPA-3299 EMC-845: Step-by-step test procedures for operation of all ...

Y R

TPA-3300 EMC-846: Special support equipment shall be made available ...

Y R

TPA-3301 EMC-847: Each item of equipment shall have met the requirem ...

Y R

TPA-3302 EMC-853: The system level requirements, imposed by this doc ...

Y R

TPA-3303 EMC-730: Each power line interface shall be designed to be ...

Y R

TPA-3304 EMC-731: Each power user shall ensure that: at electrical c ...

Y T

TPA-3305 EMC-455: For 28V busses inrush current at unit switch on sh ...

Y T

TPA-3306 EMC-457: For 28V: The transient on the primary power bus di ...

Y T

TPA-3307 EMC-459: For 28V: Conducted voltage transients on the prima ...

Y T

TPA-3308 EMC-453: The Conducted Emission requirements given below ar ...

Y R

TPA-3309 EMC-461: Conducted narrow band current emissions (different ...

Y T

TPA-3310 EMC-463: Conducted narrow band current emissions (common mo ...

Y T

TPA-3311 EMC-465: In case of internal redundancy, conducted emission ...

Y T

TPA-3312 EMC-467: Differential Mode: Time domain conducted current r ...

Y T

TPA-3313 EMC-893: Time domain conducted voltage ripple/spike on the ...

Y T

TPA-3314 EMC-468: Common Mode: The time domain conducted current ri ...

Y T

TPA-3315 EMC-469: In case of internal redundancy, time domain emissi ...

Y T

TPA-3316 EMC-473: The maximum voltage emission levels for secondary ...

Y T

TPA-3317 EMC-475: The voltage ripple and spikes on secondary power s ...

Y T

TPA-3318 EMC-464: Frequency Domain: Conducted narrow band (NB) curre ...

Y T

TPA-3319 EMC-481: Primary power bus powered units shall not exhibit ...

Y T

TPA-3320 EMC-483: Primary power bus powered units shall not exhibit ...

Y T


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TPA-3321 EMC-485: The unit shall not exhibit any failures, malfuncti ...

Y T

TPA-3322 EMC-490: When secondary lines power a unit, the unit shall ...

Y T

TPA-3323 EMC-491: When a unit delivers secondary power, the unit sha ...

Y T

TPA-3324 EMC-493: The conducted susceptibility specification for sec ...

Y T,R

TPA-3325 EMC-495: In addition, a margin of at least +6dB shall be de ...

Y T,R

TPA-3326 EMC-927: Reciever circiuts shall not respond to the followi ...

Y

TPA-3327 EMC-497: The unit shall not exceed the limits of figure EMC ...

Y T,A

TPA-3328 EMC-502: The Radiated H field generated by Units, shall not ...

Y T

TPA-3329 EMC-1342: Unit low frequency AC test requirements to achieve ...

Y T

TPA-3330 EMC-505: The unit shall not show any malfunction or deviati ...

Y T

TPA-3331 EMC-506: The unit shall not show any malfunction or deviati ...

Y T

TPA-3332 EMC-510: Units shall not show any malfunction or deviation ...

Y A

TPA-3333 EMC-838: Design rules applicable for a magnetically clean s ...

Y A,R

TPA-3334 EMC-514: The use of ferro-magnetics shall be avoided for pa ...

Y I,R

TPA-3335 EMC-516: Steel or other magnetic materials shall be avoided ...

Y T,I,R

TPA-3336 EMC-517: It is not permitted to use high permeable shieldin ...

Y

TPA-3337 EMC-518: The use of relays shall be limited to the most cri ...

Y R

TPA-3338 EMC-519: The maximum magnetic moment applicable to each uni ...

Y R

TPA-3339 EMC-522: The unit shall not be susceptible when submitted t ...

Y T

TPA-3340 EMC-323: MGSE shall not interfere with the aims of Electric ...

Y R

TPA-3341 EMC-306: All MGSE used for test purposes shall provide bond ...

Y R

TPA-3342 EMC-298: All MGSE used for electrical tests shall provide g ...

Y R

TPA-3343 EMC-308: All electromechanical devices with a safety wire c ...

Y R

TPA-3344 EMC-310: Transport containers and protective covers for the ...

Y R

TPA-3345 EMC-314: EGSE shall not interfere with the aims of Electric ...

Y R

TPA-3346 EMC-325: EMI orginated by EGSE shall be limited to such ext ...

Y T,R

TPA-3347 EMC-320: The Bonding, Grounding and Isolation of all EGSE s ...

Y R


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TPA-3348 EMC-331: Each EGSE shall include a mains isolation transfor ...

Y I

TPA-3349 EMC-332: Compliance to EN 60335-1 Class II ...

Y

TPA-3350 EMC-333: Provide galvanic isolation from the supplied Phase ...

Y T

TPA-3351 EMC-334: Provide galvanic isolation from the Industrial sup ...

Y T

TPA-3352 EMC-336: Provide a ground reference point for the isolated ...

Y T

TPA-3353 EMC-338: Provide adequate safety protection devices (See di ...

Y T

TPA-3354 EMC-382: Provide adequate Powerline filtering to ensure tha ...

Y T

TPA-3355 EMC-335: Ensure an isolation value of at least 4 kV primar ...

Y T

TPA-3356 EMC-370: The loss of any powerline shall not cause damage t ...

Y T

TPA-3357 EMC-371: Subsequent restoration of power either partially o ...

Y T

TPA-3358 EMC-372: Uninterruptable power supplies may be used only wi ...

Y R

TPA-3359 EMC-341: Each EGSE shall provide an internal ground referen ...

Y R

TPA-3360 EMC-342: Each EGSE rack/unit tester shall provide a bonding ...

Y T

TPA-3361 EMC-343: The EGSE rack housing shall be bonded to the inter ...

Y T

TPA-3362 EMC-344: The bonding stud shall be connected to the EGSE gr ...

Y T

TPA-3363 EMC-361: EGSE comprising more than one rack (e.g. at Instru ...

Y T

TPA-3364 EMC-351: EGSE signal/power circuits interfacing with onboar ...

Y T

TPA-3365 EMC-354: The signal interfaces between onboard hardware and ...

Y T

TPA-3366 EMC-352: EGSE buffer and isolation circuitry and associated ...

Y T

TPA-3367 EMC-353: Additional line drivers in the cable harness betwe ...

Y T

TPA-3368 EMC-358: The grounding of shields on interface circuits wit ...

Y T

TPA-3369 EMC-360: Signals/interfaces requiring connection to onboard ...

Y T

TPA-3370 EMC-376: All EGSE shall provide adequate AC power line inpu ...

Y T,A

TPA-3371 EMC-377: EGSE units/racks shall not compromise other EGSE w ...

Y

TPA-3372 EMC-374: All EGSE shall maintain a conducted margin of at l ...

Y T,A

TPA-3373 EMC-378: EGSE housing/racks shall be RF tight to the maximu ...

Y T,R

TPA-3374 EMC-379: No EGSE shall compromise the objective of EMC and ...

Y T,A


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TPA-3375 EMC-380: EGSE located within the anechoic chamber during an ...

Y T,A

TPA-3376 EMC-348: For each EGSE /EGSE set-up a grounding diagram sha ...

Y R

TPA-3377 EMC-154: Development tests shall be performed to evaluate t ...

Y T,R

TPA-3378 EMC-156: Qualification tests for PFM shall be performed as ...

Y T,R

TPA-3379 EMC-158: Acceptance tests for FM shall be performed as spec ...

Y T,R

TPA-3380 EMC-160: In order to ensure the proper grounding of the sec ...

Y T,R

TPA-3381 EMC-162: A re-test may be required in case a test result is ...

Y R

TPA-3382 EMC-164: The pre- and post-test inspection is specified in ...

Y R

TPA-3383 EMC-169: All EMC tests shall be conducted under standard am ...

Y R

TPA-3384 EMC-171: The test facilities used for the EMC test program ...

Y R

TPA-3385 EMC-174: The maximum allowable tolerance for the test param ...

Y R

TPA-3386 EMC-176: The accuracy of measurement equipment and test equ ...

Y R

TPA-3387 EMC-178: Grounding of Test Equipment: Measurement equipment ...

Y R

TPA-3388 EMC-179: Antenna Placement: For radiated emission measureme ...

Y R

TPA-3389 EMC-180: Receiver Bandwidth: The following receiver bandwid ...

Y R

TPA-3390 EMC-182: Power Adjustment: The primary power for unit/equip ...

Y R

TPA-3391 EMC-184: For the conducted emission and susceptibility test ...

Y R

TPA-3392 EMC-187: Each LISN has to be designed and provided by the c ...

Y T

TPA-3393 EMC-191: These particular tests shall demonstrate the compl ...

Y R

TPA-3394 EMC-192: The equipment under test shall be switched on in t ...

Y R

TPA-3395 EMC-193: For emission testing the unit/equipment shall oper ...

Y R

TPA-3396 EMC-194: For susceptibility testing the suitable operationa ...

Y R

TPA-3397 EMC-195: After testing the equipment shall be switched off ...

Y R

TPA-3398 EMC-196: Both Emission and Susceptibility operational test ...

Y R

TPA-3399 EMC-197: The particular test set-up shall represent the fli ...

Y R


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TPA-3400 EMC-199: General Aspects: Each item (from unit/equipment to ...

Y R

TPA-3401 EMC-200: Data Acquisition: The item under test shall be con ...

Y R

TPA-3402 EMC-203: This test shall verify the DC resistance of bondin ...

Y R

TPA-3403 EMC-204: The bonding test shall be performed with the unit/ ...

Y R

TPA-3404 EMC-205: The bonding test shall be performed without any ha ...

Y R

TPA-3405 EMC-863: Milliohm level bonds imposed for RF interference c ...

Y T

TPA-3406 EMC-865: All elements that could discharge, were they isola ...

Y T

TPA-3407 EMC-866: Immunity to electrostatic discharge shall be verif ...

Y T

TPA-3408 EMC-868: Control of static charging, plasma/payload induced ...

Y T,A

TPA-3409 EMC-207: This test is to measure the isolation of primary a ...

Y R

TPA-3410 EMC-208: The isolation test shall be performed with the UUT ...

Y R

TPA-3411 EMC-212: This test shall demonstrate the compliance of the ...

Y R

TPA-3412 EMC-213: UUT operation shall be selected in order to maximi ...

Y R

TPA-3413 EMC-215: Ripple and transient interference tests on the pow ...

Y R

TPA-3414 EMC-219: This test shall measure the conducted emissions (r ...

Y R


Y R

TPA-3416 EMC-221: When the secondary power provider and user need to ...

Y R


Y T

TPA-3418 EMC-229: This test shall demonstrate the noise immunit/equi ...

Y R

TPA-3419 EMC-230: The mode selection for susceptibility testing shal ...

Y R

TPA-3420 EMC-238: This test shall demonstrate the noise immunit/equi ...

Y R

TPA-3421 EMC-239: The mode selection for susceptibility testing shal ...

Y R


Y R


Y R

TPA-3424 EMC-252: This test shall demonstrate the immunity of the te ...

Y R


Y R


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TPA-3426 EMC-256: This test shall demonstrate the immunit/equipmenty ...

Y R


Y R

TPA-3428 EMC-260: The ESD test, radiated discharges, shall demonstra ...

Y R


Y R

TPA-3430 EMC-265: This test shall be used in order to show the compl ...

Y T,R

TPA-3431 EMC-267: Verification by similarity may be applied to units ...

Y A,R


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Requirement/Section Cross Reference Page numbers are the pages where the sections start

TPA-37 ............... 2.1....................7 TPA-38 ............... 2.1....................7 TPA-219 ............. 3.......................10 TPA-222 ............. 3.1....................10 TPA-223 ............. 3.1....................10 TPA-232 ............. 3.2....................10 TPA-243 ............. 3.2....................10 TPA-247 ............. 3.5.22.6............29 TPA-248 ............. 5.2....................38 TPA-249 ............. 5.2....................38 TPA-250 ............. 3.2....................10 TPA-251 ............. 3.4.3.................21 TPA-253 ............. 3.2.3.................12 TPA-255 ............. 3.2.4.................12 TPA-270 ............. 3.4.1.2..............18 TPA-273 ............. 3.2.5.................12 TPA-275 ............. 3.2.6.................12 TPA-277 ............. 3.5.24...............31 TPA-279 ............. 3.5.16...............25 TPA-286 ............. 3.5.17.2............25 TPA-288 ............. 3.5.17.3............25 TPA-290 ............. 3.5.17.4............26 TPA-292 ............. 3.5.17.5............26 TPA-294 ............. 3.5.17.6............26 TPA-298 ............. 3.5.17.7............26 TPA-303 ............. 3.4.1.7..............19 TPA-305 ............. 3.5.15...............25 TPA-308 ............. 3.5.14...............25 TPA-310 ............. 3.5.25...............31 TPA-338 ............. 3.5.4.................23 TPA-343 ............. 3.5.23...............29 TPA-347 ............. 3.5.23...............29 TPA-349 ............. 3.5.23...............29 TPA-351 ............. 3.5.23...............29 TPA-352 ............. 3.5.23...............29 TPA-355 ............. 3.5.23...............29 TPA-356 ............. 3.5.23...............29 TPA-357 ............. 3.5.23...............29 TPA-358 ............. 3.5.23...............29 TPA-359 ............. 3.5.23...............29 TPA-360 ............. 3.5.4.................23 TPA-362 ............. 4.1....................37 TPA-365 ............. 3.2.10...............14 TPA-368 ............. 3.2.10...............14 TPA-369 ............. 3.2.10...............14 TPA-370 ............. 3.2.10...............14 TPA-372 ............. 3.4.2.................20 TPA-374 ............. 3.2.2.................11 TPA-382 ............. 3.5.5.................23 TPA-383 ............. 3.5.6.................23 TPA-388 ............. 3.2.1.................11 TPA-426 ............. 3.3.1.................17 TPA-428 ............. 3.5.10...............24 TPA-429 ............. 3.5.10...............24 TPA-432 ............. 3.2.14...............17 TPA-434 ............. 3.5.11...............24 TPA-438 ............. 3.2.9.................14

TPA-443..............3.4.4 ................ 22 TPA-445..............3.2.8 ................ 13 TPA-450..............3.2.13 .............. 15 TPA-464..............3.2.13 .............. 15 TPA-470..............3.5.12 .............. 24 TPA-478..............3.5.19 .............. 26 TPA-516..............3.5.20 .............. 26 TPA-517..............3.5.20 .............. 26 TPA-543..............3.5.2 ................ 22 TPA-545..............3.5.1 ................ 22 TPA-546..............3.5.1 ................ 22 TPA-550..............3.5.7 ................ 23 TPA-557..............3.5.13 .............. 25 TPA-559..............3.5.22.4 ........... 28 TPA-561..............3.5.22.3 ........... 28 TPA-567..............3.5.22.5 ........... 28 TPA-569..............3.5.22.6 ........... 29 TPA-571..............3.6 ................... 32 TPA-574..............3.6.2 ................ 33 TPA-579..............3.6.2.1 ............. 33 TPA-580..............3.6.2.1 ............. 33 TPA-582..............3.6.2.2 ............. 33 TPA-583..............3.6.2.2 ............. 33 TPA-584..............3.6.2.2 ............. 33 TPA-585..............3.6.2.2 ............. 33 TPA-586..............3.6.2.2 ............. 33 TPA-587..............3.6.2.2 ............. 33 TPA-596..............3.6.2.4 ............. 34 TPA-614..............3.6.2.4.1 .......... 35 TPA-616..............3.6.2.4.1 .......... 35 TPA-633..............3.6.2.4.1 .......... 35 TPA-667..............3.6.2.4.1 .......... 35 TPA-682..............3.5.26 .............. 31 TPA-691..............3.5.27.1 ........... 31 TPA-754..............3.5.22.1 ........... 27 TPA-758..............3.5.22.2 ........... 28 TPA-786..............3.6.1 ................ 32 TPA-791..............3.4.1.5 ............. 19 TPA-794..............3.2.7 ................ 12 TPA-796..............3.5.22.7 ........... 29 TPA-801..............3.5.22.7.1 ........ 29 TPA-803..............3.5.22.7.2 ........ 29 TPA-805..............3.5.22.7.3 ........ 29 TPA-807..............3.4.1.4 ............. 18 TPA-849..............5.1 ................... 38 TPA-852..............5.1 ................... 38 TPA-857..............5.2 ................... 38 TPA-866..............4.2 ................... 37 TPA-870..............6.3 ................... 39 TPA-871..............6.4 ................... 39 TPA-1055............6.5 ................... 42 TPA-1057............3.6.2.4 ............. 34 TPA-1088............3.5.22.6 ........... 29 TPA-1091............3.5.22.6 ........... 29 TPA-1104............3.4.1.7 ............. 19 TPA-1106............3.5.8 ................ 24 TPA-1114............3.4.4 ................ 22

TPA-1118............ 3.5.9 .................24 TPA-1128............ 3.5.17.8 ............26 TPA-1139............ 3.5.20 ...............26 TPA-1151............ 3.4.1.6 ..............19 TPA-1155............ 6.1 ....................39 TPA-1156............ 6.1 ....................39 TPA-1157............ 6.1 ....................39 TPA-1166............ 3.5.8 .................24 TPA-1186............ 3.6.2.3 ..............34 TPA-1188............ 3.6.2.4.1 ...........35 TPA-1826............ 3.6.2.3 ..............34 TPA-2390............ 5.1 ....................38 TPA-2418............ 3.5.5 .................23 TPA-2421............ 3.5.21 ...............26 TPA-2422............ 3.5.23 ...............29 TPA-2432............ 3.2.13.2 ............17 TPA-2476............ 3.5.18 ...............26 TPA-2477............ 3.5.17.1 ............25 TPA-2601............ 3.2 ....................10 TPA-2604............ 3.2.13.1 ............17 TPA-2605............ 3.5.4 .................23 TPA-2608............ 3.4.3 .................21 TPA-2609............ 3.4.3 .................21 TPA-2645............ 3.6.1 .................32 TPA-2647............ 6.2 ....................39 TPA-2657............ 3.3.2 .................17 TPA-2683............ 3.5.23 ...............29 TPA-2685............ 3.2.2 .................11 TPA-2690............ 3.2.12 ...............15 TPA-2693............ 3.5.3 .................23 TPA-2695............ 3.6.1 .................32 TPA-2756............ 3.4.1.3 ..............18 TPA-2757............ 3.4.1.3 ..............18 TPA-2814............ 3.2.8 .................13 TPA-2816............ 3.2.11 ...............14 TPA-2817............ 3.4.1.5 ..............19 TPA-2818............ 3.4.2 .................20 TPA-2916............ 3.6.1 .................32 TPA-2917............ 3.4.2 .................20 TPA-2920............ 3.4.1.5 ..............19 TPA-2932............ 3.6.2.4.2.1 ........36 TPA-2934............ 3.6.2.4.2.2 ........36 TPA-2936............ 3.6.2.4.2.3 ........36 TPA-2938............ 3.6.2.4.2.4 ........36 TPA-2955............ 3.4.2 .................20 TPA-2959............ 3.2.7 .................12 TPA-2961............ 3.5.22.1 ............27 TPA-2962............ 3.5.22.1 ............27 TPA-2966............ 3.4.1.1 ..............18 TPA-2969............ 3.3.2 .................17 TPA-2970............ 3.6.1 .................32 TPA-3024............ 3.5.30 ...............31 TPA-3027............ 3.5.30 ...............31 TPA-3028............ 3.5.30 ...............31 TPA-3029............ 3.5.30 ...............31 TPA-3035............ 3.5.28 ...............31 TPA-3039............ 3.5.29 ...............31


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TPA-3049 ........... 3.5.22.1............27 TPA-3432 ........... 3.2.7.................12 TPA-3433 ........... 3.2.7.................12


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